A variable cycle aircraft engine axial translation type front duct ejector

Abstract

An axial translational front duct ejector of a variable cycle aircraft engine comprises: an inner casing assembly, a front duct regulating valve assembly, an outer casing assembly, an actuator assembly and a driving rocker arm assembly; the inner wall surface of the inner casing assembly constitutes an airflow channel of the front duct ejector, and the front duct regulating valve is placed at the front duct outlet through the cooperation of a guide shaft and a guide bushing; one end of the actuator assembly is fixed to the outer casing assembly, and the other end forms a ball hinge with the driving rocker arm assembly through a joint bearing, and the driving rocker arm assembly is fixed to the outer casing, and the extension or shortening of the movable end of the actuator drives the spline sleeve rocker arm on the inner casing assembly to rotate through the driving rocker arm assembly; the two ends of the adjusting connecting rod assembly are respectively connected to the spline sleeve rocker arm and the front duct regulating valve through joint bearings to form a ball hinge, which offsets the circumferential motion trend brought about by the rotation of the spline sleeve and converts it into a driving force for the axial translation of the front duct regulating valve along the guide bushing.

Description

Technical Field

[0001] The present application belongs to the field of aero-engines, and specifically relates to an axially translating front duct ejector of a variable cycle aero-engine. Background Art

[0002] The front duct ejector is one of the characteristic structures of a variable cycle aircraft engine. An annular ejector duct with a rectifying support plate is set on the compressor casing to connect the inner and outer ducts. A front duct regulating valve is set at the ejector duct outlet. According to the actual operating conditions of the aircraft engine, the opening of the front duct regulating valve is changed through the regulating mechanism to adjust the thermodynamic cycle parameters and ensure the performance indicators of the aircraft engine under complex and changeable operating conditions.

[0003] Currently, the drive mechanism of the front duct ejector of a variable cycle aircraft engine mostly utilizes the axial rotation of the active rocker arm and the passive rocker arm to drive the front duct regulating valve to move axially and rotate circumferentially at the same time, that is, to perform cylindrical secondary motion. Alternatively, the front duct regulating valve is required to move axially under ideal conditions, but the opening is adjusted in a manner that is not feasible in engineering due to lack of constraints. The existing technical solutions have the following defects:

[0004] 1) The rocker arm slide is an idealized model, lacking the constraint of the axial motion of the front duct control valve. As a result, in engineering applications, the front duct control valve will rotate circumferentially around the engine axis under the drive of the active rocker arm.

[0005] 2) The front duct regulating valve rotates circumferentially when adjusting its opening, generating significant friction between the valve and the front duct casing. This can easily cause the mechanism to become stuck, and can also cause significant friction damage to the front duct regulating valve and the front duct casing, reducing the service life of the parts.

[0006] 3) To accommodate the circumferential rotation of the front duct control valve, the active and passive rocker arms must adopt a flexible rocker arm design to compensate for radial deformation. Rigid rocker arms will cause the drive mechanism to self-lock, and deformation of the flexible rocker arm during the driving process will generate driving resistance. The reciprocating motion of the mechanism will reduce the fatigue life of the parts. At the same time, flexible deformation of the rocker arm will reduce the adjustment accuracy and cause the problem of nonlinear feedback of the adjustment.

[0007] 4) There are too many follower rockers. The auxiliary support follower rockers are distributed in more than three locations circumferentially. This will lead to overconstraint in the circumferential positioning of the front duct control valve. Overconstraint can theoretically lead to self-locking of the mechanism. In engineering, clearance must be designed to prevent self-locking, which in turn causes the drive mechanism to have idle travel problems. At the same time, the excessive number of follower rockers increases the overall weight, which does not meet the current requirements for aircraft engine weight reduction.

[0008] 5) The length of the active rocker arm cannot be adjusted. Due to the existence of manufacturing tolerances, the length deviation of the two symmetrically distributed active rocker arms will lead to poor coaxiality between the front duct control valve and the front duct casing, increase the adjustment resistance, and easily cause the mechanism to get stuck, which in turn feeds back to the actuator cylinder, causing the stroke or driving force to be out of sync, creating obstacles for the control of variable cycle parameters of aircraft engines.

[0009] Therefore, the present application is proposed to solve the above-mentioned defects of the prior art.

[0010] It should be noted that the present application is not limited to the driving mechanism or the regulating mechanism, but rather clarifies the complete structural scheme of the front duct ejector of a variable cycle aircraft engine applicable to engineering, and its regulating mechanism is novel and creative. Summary of the Invention

[0011] The purpose of this application is to provide an axially translating front duct ejector for a variable cycle aircraft engine to overcome the known technical defects.

[0012] The technical solution of this application is:

[0013] An axial translation type front duct ejector for a variable cycle aircraft engine, comprising:

[0014] The inner casing assembly includes a core engine driven fan casing, a spline sleeve rocker arm assembly, a front duct casing, a front duct casing rear section and a guide bushing; the front duct casing is an integrated whole-ring casing structure composed of an outer ring casing, a straightening support plate and an inner ring casing, the front end of the outer ring casing is positioned by a stop and fasteners connected to the core engine driven fan casing, the rear end of the inner ring casing is positioned by a stop and fasteners connected to the front duct casing rear section, the inner wall surface of the core engine driven fan casing, the inner wall surface of the outer ring casing, the straightening support plate wall surface, the outer wall surface of the inner ring casing and the outer wall surface of the front duct casing rear section together form the front duct ejector airflow channel; the spline sleeve rocker arm assembly is fixed to the outer wall surface of the core engine driven fan casing by fasteners; the guide bushing is connected to the mounting boss provided at the rear end of the outer ring casing of the front duct casing by fasteners, and a graphite filling hole is provided on the guide bushing for inlaying graphite;

[0015] The front duct regulating valve assembly includes a front duct regulating valve and an adjusting connecting rod assembly. The front duct regulating valve is a full-ring structure, sleeved on the outer periphery of the front duct casing, located at the outlet of the front duct ejector, with a guide shaft provided circumferentially on the inner wall surface and an annular mounting edge with connecting lugs provided on the outer wall surface. The guide shaft cooperates with a guide bushing installed at the rear end of the outer ring casing in the front duct casing to enable axial translation. The adjusting connecting rod assembly is connected to the connecting lug on the front duct regulating valve via fasteners.

[0016] The outer casing assembly includes an outer casing and an actuator bracket; the outer casing is located on the outer periphery of the inner casing assembly, and the actuator bracket is fixed to the outer wall of the outer casing by fasteners;

[0017] The actuator assembly includes an actuator and spherical bearings I and III. The fixed end of the actuator is articulated with the spherical bearing I and the actuator bracket, and the movable end is installed with the spherical bearing III.

[0018] The driving rocker arm assembly includes a driving rocker arm, a transmission rod, a spherical bearing II, and a pressure plate. One end of the driving rocker arm is articulated with a ball joint at the movable end of the actuator via a spherical bearing III, and the other end is connected to the upper end of the driving rod via a flat key for torque transmission and fasteners for positioning. The driving rod is mounted on the opening of the outer casing via a spherical bearing II, and an involute spline is provided at the lower end of the driving rod. The pressure plate secures the driving rod and spherical bearing II to the outer casing via fasteners.

[0019] The spline sleeve rocker arm assembly includes: a spline sleeve rocker arm, a cylindrical retainer and a front duct adjustment support; an involute spline mounting groove is provided at one end of the spline sleeve rocker arm, which is installed in conjunction with the involute spline provided at the lower end of the transmission rod to transmit torque, and a transfer lug is provided at the other end, which is connected to the adjustment connecting rod assembly; the cylindrical retainer cooperates with the openings on the spline sleeve rocker arm and the front duct adjustment support to achieve radial positioning through fasteners; the front duct adjustment support is fixed to the outer wall of the core engine drive fan casing through fasteners.

[0020] Furthermore, in the above-mentioned variable cycle aircraft engine axial translation type front duct ejector, the adjusting connecting rod assembly includes a connecting rod adjusting rod, a spherical head connecting rod A and a spherical head connecting rod B;

[0021] The spherical head connecting rod A includes a spherical head lug A and a spherical bearing IV; the spherical head connecting rod B includes a spherical head lug B and a spherical bearing V; the spherical head lug A and the spherical head lug B are connected to the two ends of the connecting rod adjusting rod through threads with opposite rotation directions, so that the adjusting connecting rod assembly can achieve continuous online length adjustment by rotating the connecting rod adjusting rod without disassembling; the spherical head lug A is connected to the adapter lug on the spline sleeve rocker arm through the spherical bearing IV ball joint; the spherical head lug B is connected to the connecting lug on the front duct regulating valve through the spherical bearing V ball joint.

[0022] Furthermore, in the above-mentioned variable cycle aircraft engine axial translation type front duct ejector, the guide shaft, guide bushing and corresponding structures on the front duct regulating valve in the front duct regulating valve assembly are evenly distributed at three locations in the circumferential direction.

[0023] Furthermore, in the above-mentioned variable cycle aircraft engine axial translation type front duct ejector, the connecting lug on the front duct regulating valve in the front duct regulating valve assembly, the actuator cylinder assembly, the driving rocker arm assembly, the adjusting connecting rod assembly in the front duct regulating valve assembly, the spline sleeve rocker arm assembly in the inner casing assembly, and the actuator cylinder bracket in the outer casing assembly and its corresponding structures are evenly distributed at two places in the circumference.

[0024] The present invention has at least the following beneficial technical effects:

[0025] 1) Fully consider the design, manufacturing and assembly processability, and possess the potential for engineering practice and technology transformation;

[0026] 2) The cooperation between the guide bushing and the guide shaft constrains the axial movement of the front duct control valve. The front duct control valve has no circumferential rotation tendency. The graphite embedded in the guide bushing can play a lubricating role during the movement of the front duct control valve, which can reduce the adjustment resistance and increase the life of the parts.

[0027] 3) Since the front duct control valve does not rotate circumferentially, the spline sleeve rocker arm and control connecting rod assembly involved in the adjustment can adopt a rigid design, avoiding fatigue life, adjustment accuracy and nonlinear feedback problems caused by flexible deformation of the adjustment mechanism transmission parts;

[0028] 4) The three circumferentially evenly distributed guide bushings will not cause circumferential over-constraint problems, which can avoid the theoretical self-locking of the mechanism and solve the problems of clearance travel and overall machine weight caused by too many auxiliary support structures;

[0029] 5) An adjusting link assembly with adjustable length and joint bearings at both ends is provided in the adjusting mechanism, which can not only connect the rotation of the spline sleeve rocker arm and the axial movement of the front duct regulating valve, but also solve the problem of coaxiality difference between the front duct regulating valve and the front duct casing caused by the manufacturing tolerance of parts during assembly, reduce the probability of the front duct regulating valve swaying and jamming, and thus prevent the occurrence of variable cycle parameter control problems of the aircraft engine caused by the asynchronous stroke of the actuator or the driving force. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 This is a schematic diagram of an axial translational front duct ejector for a variable cycle aircraft engine provided by an embodiment of the present application;

[0031] Figure 2 This is a partial schematic diagram of an axial translational front duct ejector for a variable cycle aircraft engine provided by an embodiment of the present application;

[0032] Figure 3 1. It is a top view of the outer casing assembly of the axial translation type front duct ejector of the variable cycle aircraft engine provided by an embodiment of the present application;

[0033] Figure 4 This is a top view of the inner casing assembly of the axial translation type front duct ejector of the variable cycle aircraft engine provided by an embodiment of the present application;

[0034] Figure 5 is a three-dimensional schematic diagram of a guide bushing provided in an embodiment of the present application;

[0035] Figure 6 3D schematic diagram of the front duct regulating valve provided in an embodiment of the present application;

[0036] in:

[0037] 1-Inner casing assembly; 2-Front duct regulating valve assembly; 3-Outer casing assembly; 4-Actuator assembly; 5-Drive rocker arm assembly; 6-Core engine drive fan casing; 7-Splined rocker arm assembly; 8-Front duct casing; 9-Front duct casing rear section; 10-Guide bushing; 11-Front duct regulating valve; 12-Adjusting connecting rod assembly; 13-Outer casing; 14-Actuator bracket; 15-Actuator; 16-Spherical bearing I; 17-Drive rocker arm; 18-Transmission rod; 19-Spherical bearing II; 20-Pressure plate; 21-Splined Keyed rocker arm; 22-cylindrical retaining frame; 23-front duct adjustment support; 24-connecting rod adjustment rod; 25-spherical head connecting rod A; 26-spherical head connecting rod B; 27-spherical head lug A; 28-spherical head lug B; 29-outer ring casing; 30-rectifier support plate; 31-inner ring casing; 32-mounting boss; 33-guide shaft; 34 connecting lug; 35-flat key; 36-involute spline; 37-graphite filling hole; 38-spherical bearing III; 39-adapter lug; 40-spherical bearing IV; 41-spherical bearing V; 42-double fork lug.

[0038] To better illustrate this embodiment, the drawings omit fasteners (bolts, nuts, pins) and other minor design details. Some components may be enlarged or reduced in size and do not represent the actual product size. In addition, the drawings are for illustrative purposes only and should not be construed as limitations on this application. DETAILED DESCRIPTION

[0039] To make the technical solution and its advantages of the present application clearer, the technical solution of the present application will be described in further detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of the present application and are only used to explain the present application, not to limit the present application. It should be noted that, for ease of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0040] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those skilled in the art in the field to which this application belongs. The words "upper", "lower", "front", "back", "inside", "outside" and the like used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships, and do not imply that the device or component must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore cannot be understood as a limitation on this application. "Including" used in the description of this application means that the components appearing after the word are assembly sub-items of the components preceding the word.

[0041] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense, which can be a fixed connection or a detachable connection, etc. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0042] The following is combined with Figures 1 to 6 This application is described in further detail.

[0043] An axial translation type front duct ejector for a variable cycle aircraft engine, comprising:

[0044] Inner casing assembly 1, front duct regulating valve assembly 2, outer casing assembly 3, actuator assembly 4, driving rocker arm assembly 5.

[0045] The inner wall surface of the core engine drive fan 6 in the inner casing assembly 1, the inner wall surface of the outer ring casing 29 in the front duct casing 8, the wall surface of the straightening support plate 30, the outer wall surface of the inner ring casing 31 and the outer wall surface of the front duct casing rear section 9 constitute the front duct ejector airflow channel. The front duct regulating valve 11 in the front duct regulating valve assembly 2 is arranged at the outlet of the front duct ejector. The opening of the front duct regulating valve 11 is changed by the regulating mechanism to realize the variable cycle characteristics of the aircraft engine.

[0046] In order to constrain the axial translation of the front duct regulating valve 11, three guide shafts 33 are evenly distributed on its inner wall surface along the circumferential direction. A mounting boss 32 is set at the corresponding circumferential position of the rear section of the outer ring casing 29 to place the guide bushing 10. The guide bushing 10 and the guide shaft 33 cooperate to strictly ensure the axial translation of the front duct regulating valve 11. In order to reduce the adjustment resistance caused by friction, a graphite filling hole 36 is set on the guide bushing 10 for filling graphite, which plays a role in sufficient lubrication during the axial reciprocating motion of the front duct regulating valve 11.

[0047] As the driving device of the adjustment mechanism, one end of the actuator 15 is ball-hinged on the actuator bracket 14 through the joint bearing I16. The actuator bracket 14 is fixed to the outer casing 13 through fasteners. The movable end of the actuator 15 is ball-hinged with the double fork ear 42 on the driving rocker arm 17 through the joint bearing III (38).

[0048] The driving rocker arm assembly 5, the spline sleeve rocker arm assembly 7 and the adjusting connecting rod assembly 12 together constitute the transmission device of the adjusting mechanism, wherein the driving rocker arm assembly 7 is fixed to the outer casing 13 through the pressure plate 20, the transmission rod 18 cooperates with the outer casing 13 through the joint bearing II19, one end of the transmission rod 18 is connected to the driving rocker arm 17 through a flat key 35 to transmit torque, and an involute spline 36 is provided at the other end of the transmission rod 18.

[0049] The spline sleeve rocker arm assembly 7 is fixed to the outer wall of the core engine drive fan casing 6 through the front duct adjustment support 23. The spline sleeve rocker arm 21 and the front duct adjustment bracket 23 are connected by the cylindrical retaining frame 22 and radially positioned by fasteners; a transfer lug 39 is provided at one end of the spline sleeve rocker arm 21 and is ball-hinged with the adjustment connecting rod assembly 12 through the spherical joint bearing IV40, and a mounting groove is provided at the other end to cooperate with the involute spline 36 on the transmission rod 18 to transmit torque.

[0050] The adjusting link assembly 12 includes an adjusting link 24, a spherical head link A25, and a spherical head link B26. The adjusting link 24 is connected to the spherical head link A25 and the spherical head link B26 through threads. The threads on the spherical head link A25 and the spherical head link B26 have opposite rotation directions, so that the adjusting link assembly 12 can achieve continuous online length adjustment by rotating the link adjusting rod 24 without disassembling. The spherical head link A25 and the spherical head link B26 are respectively installed with joint bearings IV40 and V41.

[0051] Under the design state, the connection between the actuator support 14 and the actuator 15 is a spherical pair, the connection between the actuator 15 and the driving rocker arm 17 is a spherical pair, the driving rocker arm 17, the transmission rod 18 and the spline sleeve rocker arm 21 are fixed pairs, and the three as a whole form a rotating pair with the axis of the cylindrical retainer 22, the connection between the adjusting connecting rod assembly 12 and the spline sleeve rocker arm 21 is a spherical pair, the connection between the front duct regulating valve 11 and the adjusting connecting rod assembly 12 is a spherical pair, and the front duct regulating valve 11 and the guide bushing 10 cooperate to form a translation pair along the axial direction.

[0052] The working mode of the front duct ejector is: the extension or shortening of the movable end of the actuator cylinder 15 is converted into the rotational motion of the driving rocker arm 17 around the axis of the cylindrical retainer 22 under the combined action of the spherical pairs at both ends of the actuator cylinder 15 and the rotating pairs of the driving rocker arm 17. The driving rocker arm 17 drives the spline sleeve rocker arm 21 to rotate coaxially through the fixed pair of the transmission rod 18. The spherical pairs at both ends of the adjusting connecting rod assembly 12 offset the circumferential motion trend brought about by the rotation of the spline sleeve rocker arm 21, and converts the axial rotation of the spline sleeve rocker arm 21 into a driving force for the axial translation of the front duct regulating valve 11 along the guide bushing 10.

[0053] During the adjustment process of the front duct ejector, there is no flexible deformation of the transmission components, and a rigid design can be adopted.

[0054] The guide bushing 10 and the guide shafts 33 on the front duct regulating valve 11 are evenly distributed at three locations along the circumferential direction to realize the circumferential positioning constraint of the front duct regulating valve 11.

[0055] The actuator assembly 4, the driving rocker arm assembly 5, the spline sleeve rocker arm assembly 7, the adjusting connecting rod assembly 12, the actuator bracket and the connecting lugs 34 on the front duct regulating valve 11 are evenly distributed at two locations along the circumference to achieve driving force balance, ensuring that the front duct regulating valve 11 does not deflect or get stuck during axial translation.

[0056] The length of the adjusting connecting rod assembly 12 is adjustable, which improves the coaxiality of the front duct regulating valve 11 and the engine axis while fully avoiding manufacturing tolerances, thereby ensuring the stability of the axial translation of the front duct regulating valve 11.

[0057] The spherical bearing II19 and the involute spline 36 ensure that the driving rocker arm assembly 5 can be assembled with the spline sleeve rocker arm 21 under the conditions of considering manufacturing tolerances.

[0058] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A variable cycle aircraft engine axial translation type front duct ejector, characterized in that: include: The inner casing assembly (1) includes a core engine driven fan casing (6), a spline sleeve rocker arm assembly (7), a front duct casing (8), a front duct casing rear section (9) and a guide bushing (10); the front duct casing (8) is an integrated ring structure composed of an outer ring casing (29), a rectifier support plate (30) and an inner ring casing (31); the front end of the outer ring casing (29) is positioned by a stop and fastened with a fastener to connect to the core engine driven fan casing (6); the rear end of the inner ring casing (31) is positioned by a stop and fastened with a fastener to connect to the front duct casing rear section (9); the core engine driven fan casing (6) is provided with ... core engine driven fan casing (6) is provided with a core engine driven fan casing (6), a spline sleeve rocker arm assembly (7), a front duct casing (8), a front duct casing rear section (9) and a guide bushing (10); the core engine driven fan casing (6) is provided with a core engine driven fan casing (6), a spline sleeve rocker arm assembly (7), a front duct casing The inner wall surface of the driving fan casing (6), the inner wall surface of the outer ring casing (29), the wall surface of the rectifying support plate (30), the outer wall surface of the inner ring casing (31) and the outer wall surface of the rear section (9) of the front duct casing jointly form the front duct ejector airflow channel; the spline sleeve rocker arm assembly (7) is fixed to the outer wall surface of the core engine driving fan casing (6) by fasteners; the guide bushing (10) is connected to the mounting boss (32) provided at the rear end of the outer ring casing (29) of the front duct casing (8) by fasteners, and a graphite filling hole (37) is provided on the guide bushing (10) for inlaying graphite; A front duct regulating valve assembly (2) comprises a front duct regulating valve (11) and an adjusting connecting rod assembly (12); the front duct regulating valve (11) is a full-ring structure, sleeved on the outer periphery of the front duct casing (8), and located at the outlet of the front duct ejector, with a guide shaft (33) provided on the inner wall surface along the circumferential direction, and an annular mounting edge with a connecting lug (34) provided on the outer wall surface; the guide shaft (33) cooperates with a guide bushing (10) installed at the rear end of the outer ring casing (29) in the front duct casing (8) and can perform axial translation; the adjusting connecting rod assembly (12) is connected to the connecting lug (34) on the front duct regulating valve (11) through a fastener; The outer casing assembly (3) includes an outer casing (13) and an actuator bracket (14); the outer casing (13) is located on the outer periphery of the inner casing assembly (1), and the actuator bracket (14) is fixed to the outer wall of the outer casing (13) by fasteners; The actuator assembly (4) includes an actuator (15), a joint bearing I (16), and a joint bearing III (38); the fixed end of the actuator (15) is spherically hinged to the actuator bracket (14) through the joint bearing I (16), and the movable end is mounted with the joint bearing III (38); The driving rocker arm assembly (5) comprises a driving rocker arm (17), a transmission rod (18), a joint bearing II (19) and a pressure plate (20); one end of the driving rocker arm (17) is connected to a ball hinge at the movable end of the actuator (15) through a joint bearing III (38), and the other end is connected to the upper end of the driving rod (18) by a flat key (35) for torque transmission and a fastener for positioning; the driving rod (18) is installed on the opening of the outer casing (13) through the joint bearing II (19), and an involute spline (36) is provided at the lower end of the driving rod (18); the pressure plate (20) fixes the driving rod (18) and the joint bearing II (19) to the outer casing (13) through fasteners; A spline sleeve rocker arm assembly (7) comprises a spline sleeve rocker arm (21), a cylindrical retainer (22) and a front duct adjustment support (23); an involute spline mounting groove is provided at one end of the spline sleeve rocker arm (21) and is mounted in conjunction with an involute spline (36) provided at the lower end of a transmission rod (18) for torque transmission; a transfer lug (39) is provided at the other end, and the transfer lug (39) is connected to an adjustment connecting rod assembly (12); the cylindrical retainer (22) is matched with openings on the spline sleeve rocker arm (21) and the front duct adjustment support (23) to achieve radial positioning through fasteners; the front duct adjustment support (23) is fixed to the outer wall surface of the core engine drive fan casing (6) through fasteners; An adjusting connecting rod assembly (12) comprising a connecting rod adjusting rod (24), a spherical head connecting rod A (25) and a spherical head connecting rod B (26); The spherical head connecting rod A (25) comprises a spherical head lug A (27) and a joint bearing IV (40); the spherical head connecting rod B (26) comprises a spherical head lug B (28) and a joint bearing V (41); the spherical head lug A (27) and the spherical head lug B (28) are connected to the two ends of the connecting rod adjusting rod (24) through threads with opposite rotation directions, so that the adjusting connecting rod assembly (12) can achieve continuous online adjustment of the length by rotating the connecting rod adjusting rod (24) in an undisassembled state; the spherical head lug A (27) is connected to the transfer lug (39) on the spline sleeve rocker arm (21) through a spherical hinge of the joint bearing IV (40); the spherical head lug B (28) is connected to the connecting lug (34) on the front duct regulating valve (11) through a spherical hinge of the joint bearing V (41).

2. The variable cycle aircraft engine axial translation type front duct ejector according to claim 1, characterized in that: The guide shaft (33), the guide bushing (10) and the corresponding structures on the front duct regulating valve (11) in the front duct regulating valve assembly (2) are evenly distributed at three locations along the circumference.

3. The variable cycle aircraft engine axial translation type front duct ejector according to claim 1, characterized in that: The connecting lug (34) on the front duct regulating valve (11) in the front duct regulating valve assembly (2), the actuator assembly (4), the driving rocker arm assembly (5), the adjusting connecting rod assembly (12) in the front duct regulating valve assembly (2), the spline sleeve rocker arm assembly (7) in the inner casing assembly (1), and the actuator bracket (14) in the outer casing assembly (3) and their corresponding structures are evenly distributed at two locations along the circumference.

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