A linkage adjustment mechanism for variable guide vanes of an aircraft engine

Abstract

The application provides a linkage adjusting mechanism of an aero-engine adjustable guide vane, and belongs to the technical field of aero-engine adjusting mechanisms, and specifically comprises: a casing, wherein the adjustable guide vane is installed on the casing, the length direction of the adjustable guide vane extends along the radial direction of the casing, and the inside of the side wall of the part of the casing for installing the adjustable guide vane is provided with an annular cavity; a thermal expansion ring is installed in the annular cavity, the rotating shaft of the adjustable guide vane penetrates through the inner wall of the casing, the thermal expansion ring and the outer wall of the casing along the radial direction of the casing, the rotating shaft side wall of the adjustable guide vane is provided with a spiral protrusion which is wrapped around the rotating shaft of the adjustable guide vane, the thermal expansion ring is provided with a through hole for the rotating shaft of the adjustable guide vane to penetrate through, and the inner wall of the through hole is provided with a spiral groove which is screwedly matched with the spiral protrusion; and a temperature adjusting structure is used for heating or cooling the thermal expansion ring. Through the processing scheme, the structural complexity of the adjusting mechanism and the occupied structural design space are reduced.

Description

Technical Field

[0001] The present application relates to the field of aircraft engine adjustment mechanisms, and in particular to a linkage adjustment mechanism for adjustable guide vanes of an aircraft engine. Background Art

[0002] The current structure and operating principle of the linkage adjustment mechanism in aircraft engines is that the actuator first drives the linkage ring, which then drives the slave rocker arm, which finally rotates the adjustable guide vanes to achieve adjustment. This existing structure requires a large design space, and the actuator is large in size, weight, and thrust requirements. It also requires numerous parts, including the master and slave rocker arms and rotating shafts. Summary of the Invention

[0003] In view of this, the present application provides a linkage adjustment mechanism for adjustable guide vanes of an aircraft engine, which solves the problems in the prior art and reduces the structural complexity of the adjustment mechanism and the structural design space occupied.

[0004] The application provides a linkage adjustment mechanism for adjustable guide vanes of an aircraft engine, which adopts the following technical solution:

[0005] A linkage adjustment mechanism for adjustable guide vanes of an aircraft engine, comprising:

[0006] A casing, wherein the adjustable guide vane is mounted on the casing, wherein the length direction of the adjustable guide vane extends along the radial direction of the casing, and an annular cavity is provided inside the side wall of the casing for mounting the adjustable guide vane;

[0007] a thermal expansion ring installed in the annular cavity; a rotating shaft of the adjustable guide vane passing through the inner wall of the casing, the thermal expansion ring, and the outer wall of the casing in a radial direction of the casing; a spiral protrusion surrounding the rotating shaft of the adjustable guide vane is provided on a side wall of the rotating shaft of the adjustable guide vane; a through hole for the rotating shaft of the adjustable guide vane to pass through is provided on the thermal expansion ring; and a spiral groove is provided on an inner wall of the through hole to cooperate with the spiral protrusion;

[0008] The temperature regulating structure heats or cools the thermal expansion ring.

[0009] Optionally, the casing is provided with an air intake chamber connected to the annular cavity, the air intake chamber includes an inlet chamber and a mixing chamber, one end of the inlet chamber is connected to the mixing chamber, and the other end of the inlet chamber is provided with a partition plate, and the partition plate divides the inlet chamber into a low-temperature gas inlet and a high-temperature gas inlet, and the end of the mixing chamber away from the inlet chamber is connected to one side of the annular cavity, and the other side of the annular cavity is provided with a gas outlet.

[0010] Optionally, the partition plate includes a fixing part and an adjusting part arranged in sequence along the air intake direction, the rotating shaft of the adjusting part is rotatably installed on the fixing part, and a driving member is provided on the outside of the casing, and the driving member drives the adjusting part to swing toward the low-temperature gas inlet side or the high-temperature gas inlet side.

[0011] Optionally, low-temperature air bleed holes are opened on the casing walls of the zeroth to second stages of the casing, and channels connecting the low-temperature air bleed holes and the low-temperature gas inlet are provided in the side walls of the casing. High-temperature air bleed holes are opened on the casing walls of the fourth to sixth stages of the casing, and channels connecting the high-temperature air bleed holes and the high-temperature gas inlet are provided in the side walls of the casing.

[0012] Optionally, a heat insulation layer is provided on the inner wall of the annular cavity.

[0013] Optionally, the thermal expansion ring is hollow.

[0014] Optionally, the rise angle of the spiral protrusion ranges from 30° to 80°.

[0015] Optionally, the rotating shaft of the adjustable guide vane is provided with a plurality of spiral protrusions distributed circumferentially along the rotating shaft of the adjustable guide vane.

[0016] In summary, this application has the following beneficial technical effects:

[0017] The radial dimensions of the thermal expansion ring change due to expansion or contraction. The spiral groove moves radially away from or closer to the axis of the casing, and the groove moves lengthwise relative to the guide vane's axis of rotation. The spiral groove acts like a nut on a screw. The movement of the spiral groove, combined with the spiral protrusion, forces the axis of rotation of the adjustable guide vane, thereby driving the adjustable guide vane. By controlling the temperature change of the thermal expansion ring to drive the guide vane, compared to directly driving the guide vane through the actuator, numerous components, such as the active and passive rocker arms, pins, and ball joints, are omitted, simplifying the structure and saving design space. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0019] Figure 1 This is a schematic diagram of the overall structure of the linkage adjustment mechanism of the adjustable guide vanes of the aircraft engine of this application;

[0020] Figure 2 This is a schematic diagram of the structure of the adjustable guide vane and thermal expansion ring of this application;

[0021] Figure 3 This is a schematic structural diagram of the annular cavity and inlet cavity of this application.

[0022] Explanation of the accompanying reference numerals: 1. Casing; 11. Annular cavity; 12. Adjustable guide vane; 13. Rotating shaft; 14. Spiral protrusion; 2. Thermal expansion ring; 21. Through hole; 22. Spiral groove; 3. Air inlet cavity; 31. Inlet cavity; 32. Mixing cavity; 33. Partition plate; 34. Low-temperature gas inlet; 35. High-temperature gas inlet; 36. Gas outlet; 37. Fixing part; 38. Adjusting part; 4. Thermal insulation layer. DETAILED DESCRIPTION

[0023] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0024] The following describes the embodiments of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the features in the following embodiments and embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without making creative work are within the scope of protection of this application.

[0025] It should be noted that various aspects of the embodiments within the scope of the appended claims are described below. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is merely illustrative. Based on this application, it should be understood by those skilled in the art that an aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects described herein can be used to implement the device and / or practice the method. In addition, other structures and / or functionalities other than one or more of the aspects described herein can be used to implement this device and / or practice this method.

[0026] It should also be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present application. The illustrations only show components related to the present application and are not drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component can be changed at will, and the component layout type may also be more complicated.

[0027] Additionally, in the following description, specific details are provided to provide a thorough understanding of the examples. However, one skilled in the art will appreciate that the aspects described can be practiced without these specific details.

[0028] An embodiment of the present application provides a linkage adjustment mechanism for adjustable guide vanes of an aircraft engine.

[0029] like Figure 1-Figure 3 As shown, a linkage adjustment mechanism for adjustable guide vanes of an aircraft engine comprises:

[0030] The casing 1 has the adjustable guide vanes 12 mounted thereon, the length direction of the adjustable guide vanes 12 extending along the radial direction of the casing 1 , and an annular cavity 11 is provided inside the side wall of the casing 1 for mounting the adjustable guide vanes 12 .

[0031] The thermal expansion ring 2 is installed in the annular cavity 11, and the rotating shaft 13 of the adjustable guide vane 12 passes through the inner wall of the casing 1, the thermal expansion ring 2 and the outer wall of the casing 1 in the radial direction of the casing 1. The side wall of the rotating shaft 13 of the adjustable guide vane 12 is provided with a spiral protrusion 14 surrounding the rotating shaft 13 of the adjustable guide vane 12. The thermal expansion ring 2 is provided with a through hole 21 for the rotating shaft 13 of the adjustable guide vane 12 to pass through, and the inner wall of the through hole 21 is provided with a spiral groove 22 that cooperates with the spiral protrusion 14. The cooperation between the spiral protrusion 14 and the spiral groove 22 is similar to that between a screw and a nut.

[0032] The temperature regulating structure heats or cools the thermal expansion ring 2 .

[0033] The radial dimension of the thermal expansion ring 2 changes due to expansion or contraction, and the spiral groove 22 moves radially away from or closer to the axis of the casing 1. The spiral groove 22 moves lengthwise relative to the guide vane's rotational axis 13. The spiral groove 22 acts like a nut on a screw. The movement of the spiral groove 22, in conjunction with the spiral protrusion 14, forces the rotational axis 13 of the adjustable guide vane 12 to rotate, thereby driving the adjustable guide vane 12. By controlling the temperature change of the thermal expansion ring 2 to drive the guide vane rotation, compared to directly driving the guide vane with an actuator, numerous components such as the active and passive rocker arms, pins, and ball heads are omitted, simplifying the structure and saving design space.

[0034] The casing 1 is provided with an air intake chamber 3 connected to the annular cavity 11, and the air intake chamber 3 includes an inlet chamber 31 and a mixing chamber 32. One end of the inlet chamber 31 is connected to the mixing chamber 32, and the other end of the inlet chamber 31 is provided with a partition plate 33. The partition plate 33 divides the inlet chamber 31 into a low-temperature gas inlet 34 and a high-temperature gas inlet 35. The end of the mixing chamber 32 away from the inlet chamber 31 is connected to one side of the annular cavity 11, and the other side of the annular cavity 11 is provided with a gas outlet 36.

[0035] Low-temperature air bleed holes are opened on the walls of the zero to two stages of the casing 1, and a channel connecting the low-temperature air bleed holes and the low-temperature gas inlet 34 is provided in the side wall of the casing 1. High-temperature air bleed holes are opened on the walls of the four to six stages of the casing 1, and a channel connecting the high-temperature air bleed holes and the high-temperature gas inlet 35 is provided in the side wall of the casing 1.

[0036] In this embodiment of the present application, airflows of different temperatures at different locations within the engine are utilized. Low-temperature gas enters the mixing chamber 32 through low-temperature air bleed holes and a low-temperature gas inlet 34, while high-temperature gas enters the mixing chamber 32 through high-temperature air bleed holes and a high-temperature gas inlet 35. The gas in the mixing chamber 32 enters the annular cavity 11, heating or cooling the thermal expansion ring 2 before being discharged from the gas outlet 36. Adjusting the amount of airflow entering the low-temperature gas inlet 34 and the high-temperature gas inlet 35 can adjust the temperature of the gas in the mixing chamber 32, thereby adjusting the temperature of the annular cavity 11. The temperature change of the annular cavity 11 can regulate the temperature of the thermal expansion ring 2. The airflow can be combustion gases of different temperatures within the casing 1.

[0037] In one embodiment, the partition plate 33 includes a fixing portion 37 and an adjusting portion 38 sequentially arranged along the air intake direction. The rotating shaft of the adjusting portion 38 is rotatably mounted on the fixing portion 37. A driving member is provided on the outside of the casing 1, and the driving member drives the adjusting portion 38 to swing toward the low-temperature gas inlet 34 or the high-temperature gas inlet 35. The spacer plate 33 extends radially along the casing 1. A motor is mounted on the outside of the casing 1, with its output shaft extending radially into the cavity 31 and connected to a rotating shaft on the adjusting portion 38 that is rotatably connected to the fixed portion 37, thereby driving the adjusting portion 38 to rotate. Alternatively, the spacer plate 33 may extend longitudinally along the casing 1, with an actuator and connecting rod driving the adjusting portion 38 to rotate about the fixed portion 37. Specifically, the actuator is mounted on a side wall surface, with its telescopic shaft extending into the inlet cavity 31 and rotatably connected to one end of the connecting rod, while the other end of the connecting rod is rotatably connected to the adjusting portion 38. The rotating axes of the telescopic shaft and the connecting rod, the connecting rod and the adjusting portion 38, and the adjusting portion 38 about the fixed portion 37 are all parallel. Driving the adjusting portion 38 to rotate does not require a high-thrust actuator. Compared to directly driving the guide vanes with the actuator, the actuator's bulk is reduced, saving space.

[0038] The inner wall of the annular cavity 11 is provided with a thermal insulation layer 4. The radial dimensions of the thermal expansion ring 2 change due to expansion or contraction. However, the thermal insulation layer 4 on the inner wall of the annular cavity 11 minimizes the impact of the mixed gas on the radial dimensions of the casing 1. The hollow design of the thermal expansion ring 2 facilitates a wide range of contraction and expansion of the thermal expansion ring 2 during temperature fluctuations.

[0039] The lead angle of the spiral protrusion 14 is in the range of 30-80 degrees, preferably 45-65 degrees. The lead angle of the spiral protrusion 14 needs to be controlled so that the movement of the spiral groove 22 can drive the spiral protrusion to rotate. It is necessary to avoid a situation where the lead angle is too small, causing self-locking and the spiral groove 22 cannot drive the spiral protrusion 14 to rotate when it moves. It is also necessary to avoid a situation where the lead angle is too large, causing the spiral groove 22 to move a large distance and only drive the spiral protrusion 14 to rotate slightly.

[0040] The rotating shaft 13 of the adjustable guide vane 12 is provided with multiple spiral protrusions 14 distributed circumferentially along the rotating shaft 13 of the adjustable guide vane 12. The spirals are right-handed. When the thermal expansion ring 2 expands, the guide vane rotates toward the engine axis, i.e., when viewed from the top of the guide vane toward the bottom of the guide vane, it rotates clockwise. The multiple spiral protrusions 14 are arranged at the same axial height along the rotating shaft 13 of the adjustable guide vane 12. In other words, the multiple spiral protrusions 14 are evenly distributed circumferentially along the rotating shaft of the guide vane, and each spiral protrusion 14 has a consistent length, width, thickness, and lead angle.

[0041] In order to achieve a larger adjustable blade angle, the following methods can be adopted: increase the adjustment range of the mixed gas temperature; use a material with a larger linear expansion coefficient for the thermal expansion ring 2; and adjust the helical angles of the spiral protrusion 14 and the spiral groove 22.

[0042] The implementation steps of the linkage adjustment mechanism of the adjustable guide vanes of the aircraft engine of the present application include: Step 1, based on a stable state, that is, the mixed gas temperature obtained by the known temperatures of the cold and hot gases and the position of the adjustment part 38;

[0043] Step 2: Set the expected rotation angle and rotation direction of the guide vane;

[0044] Step 3: Calculate the required radial deformation of the thermal expansion ring 2 according to the helix angle;

[0045] Step 4: Determine the required gas temperature change and the expected mixed gas temperature based on the radial size of the thermal expansion ring 2, the material thermal expansion coefficient, and the expected radial deformation;

[0046] Step 5: Rotate the regulating part 38 and monitor the temperature of the mixed gas to achieve the desired regulation.

[0047] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A linkage adjustment mechanism for adjustable guide vanes of an aircraft engine, characterized in that: include: A casing, wherein the adjustable guide vane is mounted on the casing, wherein the length direction of the adjustable guide vane extends along the radial direction of the casing, and an annular cavity is provided inside the side wall of the casing for mounting the adjustable guide vane; a thermal expansion ring installed in the annular cavity; a rotating shaft of the adjustable guide vane passing through the inner wall of the casing, the thermal expansion ring, and the outer wall of the casing in a radial direction of the casing; a spiral protrusion surrounding the rotating shaft of the adjustable guide vane is provided on a side wall of the rotating shaft of the adjustable guide vane; a through hole for the rotating shaft of the adjustable guide vane to pass through is provided on the thermal expansion ring; and a spiral groove is provided on an inner wall of the through hole to cooperate with the spiral protrusion; A temperature regulating structure is provided for heating or cooling the thermal expansion ring; an air intake chamber is provided on the casing and is connected to the annular cavity, the air intake chamber comprising an inlet chamber and a mixing chamber, one end of the inlet chamber is connected to the mixing chamber, and the other end of the inlet chamber is provided with a partition plate, the partition plate divides the inlet chamber into a low-temperature gas inlet and a high-temperature gas inlet, the end of the mixing chamber away from the inlet chamber is connected to one side of the annular cavity, and the other side of the annular cavity is provided with a gas outlet; The partition plate includes a fixing portion and an adjusting portion sequentially arranged along the air intake direction. The rotating shaft of the adjusting portion is rotatably mounted on the fixing portion. A driving member is provided on the outside of the casing. The driving member drives the adjusting portion to swing toward the low-temperature gas inlet side or the high-temperature gas inlet side.

2. The linkage adjustment mechanism of the adjustable guide vanes of an aircraft engine according to claim 1, characterized in that: Low-temperature air bleed holes are provided on the casing walls of the zeroth to second stages of the casing, and channels connecting the low-temperature air bleed holes and the low-temperature gas inlet are provided in the side walls of the casing. High-temperature air bleed holes are provided on the casing walls of the fourth to sixth stages of the casing, and channels connecting the high-temperature air bleed holes and the high-temperature gas inlet are provided in the side walls of the casing.

3. The linkage adjustment mechanism of the adjustable guide vanes of an aircraft engine according to claim 1, characterized in that: The inner wall of the annular cavity is provided with a heat insulation layer.

4. The linkage adjustment mechanism for adjustable guide vanes of an aircraft engine according to claim 1, characterized in that: The thermal expansion ring is hollow.

5. The linkage adjustment mechanism of the adjustable guide vanes of an aircraft engine according to claim 1, characterized in that: The rise angle of the spiral protrusion ranges from 30° to 80°.

6. The linkage adjustment mechanism of the adjustable guide vanes of an aircraft engine according to claim 1, characterized in that: The rotating shaft of the adjustable guide vane is provided with a plurality of spiral protrusions distributed along the circumference of the rotating shaft of the adjustable guide vane.

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