A cooling method for turbine guide vane of an aircraft engine

Abstract

The present application discloses a method for cooling a turbine guide vane of an aircraft engine, which belongs to the technical field of aircraft engine cooling. The method is applied to the guide vane of an aircraft engine, and the guide vane is provided with a cooling cavity. The method comprises: installing a cooling pipe, a heat exchanger and an electromagnetic pump in the turbine brake of the aircraft engine, and adding coolant to the cooling pipe, wherein the heat exchanger and the electromagnetic pump are connected in series in the cooling pipe, and the cooling cavity in the guide vane is connected to the cooling pipe through more than two connecting pipes installed on the cooling pipe; starting the electromagnetic pump so that the coolant flows from the cooling pipe through the connecting pipe into the cooling cavity of the guide vane, and then the coolant returns from the cooling cavity in the guide vane to the cooling pipe through another connecting pipe. The present application achieves the purpose of facilitating the cooling of the guide vane by starting the electromagnetic pump so that the cooling liquid flows into the cooling cavity of the guide vane through the connecting pipe.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft engine cooling, and in particular to a method for cooling aircraft engine turbine guide vane. Background Art

[0002] With the continuous development of modern aviation industry, aircraft engines are developing towards high thrust-to-weight ratio, high efficiency, high reliability and low fuel consumption. Increasing the turbine inlet temperature can effectively increase the thrust-to-weight ratio. At the same time, as the turbine inlet temperature increases, it far exceeds the heat resistance temperature of the turbine material. It is necessary to use the guide vane cooling technology to cool the guide vane temperature in the turbine gate to a lower range.

[0003] The current cooling method for the hot end components of aircraft engines is to introduce cold air into the aircraft engine through the secondary air system. The internal air then enters from the compressor drum hole, flows into the axial channel through the high-speed rotating compressor disc cavity, and finally flows through the turbine disc cavity and the guide vane. This air introduction method will produce a series of pressure losses, and the temperature of the cold air will increase accordingly. In addition, the increasingly complex guide vane structure will increase the manufacturing cost. Summary of the invention

[0004] In order to facilitate the cooling of the guide vanes, the present application provides a method for cooling the guide vanes of an aircraft engine turbine.

[0005] The present application provides a method for cooling the turbine guide vane of an aero-engine using the following technical solution:

[0006] A method for cooling a turbine guide vane of an aeroengine, the method being applied to a guide vane of an aeroengine, the guide vane being provided with a cooling cavity, the method comprising:

[0007] A cooling pipe, a heat exchanger and an electromagnetic pump are installed on the turbine brake of the aircraft engine, and coolant is added to the cooling pipe, wherein the heat exchanger and the electromagnetic pump are connected in series to the cooling pipe, and the cooling cavity in the guide vane is connected to the cooling pipe through more than two connecting pipes installed on the cooling pipe;

[0008] The electromagnetic pump is started to make the coolant flow from the cooling pipeline through the connecting pipe into the cooling cavity of the guide vane, and then the coolant returns from the cooling cavity in the guide vane through another connecting pipe to the cooling pipeline.

[0009] By adopting the above technical solution, in order to facilitate the cooling of the guide blades, the electromagnetic pump is started to drive the cooling liquid in the cooling pipe to circulate, so that the cooling liquid flows into the cooling cavity of the guide blade through the connecting pipe, and then returns to the cooling pipe from the cooling cavity of the guide blade through the connecting pipe, thereby achieving the purpose of facilitating the cooling of the guide blades.

[0010] Preferably, the thickness of the leading edge of the guide vane is greater than the thickness of the trailing edge, and the cooling cavity of the guide vane includes a leading edge cavity, a trailing edge cavity and a bottom cavity, the leading edge cavity is connected with the bottom cavity through a first cooling channel, and the bottom cavity is connected with the trailing edge cavity through a second cooling channel;

[0011] The method in which the coolant flows through the cooling cavity in the guide vane includes:

[0012] The coolant passes through the leading edge cavity, the first cooling channel, the bottom cavity, the second cooling channel, and the trailing edge cavity in sequence through the connecting pipe, and then returns to the cooling pipeline through the connecting pipe;

[0013] or;

[0014] The coolant passes through the trailing edge cavity, the second cooling channel, the bottom cavity, the first cooling channel, and the leading edge cavity in sequence through the connecting pipe, and then returns to the cooling pipeline through the connecting pipe.

[0015] By adopting the above technical solution, in the process of cooling the guide vane with coolant, the coolant can pass through the leading edge cavity, the first cooling channel, the bottom chamber, the second cooling channel, and the trailing edge cavity, so that the coolant can quickly pass through multiple parts of the guide vane, thereby facilitating the cooling of the guide vane.

[0016] Preferably, the thickness of the leading edge of the guide vane is greater than the thickness of the trailing edge, and the cooling cavity of the guide vane includes a leading edge cavity, a transition cavity, a trailing edge cavity, a leading edge bottom cavity and a trailing edge bottom cavity, the leading edge cavity is connected with the leading edge bottom cavity through a third cooling channel, the leading edge bottom cavity is connected with the transition cavity through a fourth cooling channel, the transition cavity is connected with the trailing edge bottom cavity through a fifth cooling channel, and the trailing edge bottom cavity is connected with the trailing edge cavity through a sixth cooling channel;

[0017] The method in which the coolant flows through the cooling cavity in the guide vane includes:

[0018] The coolant passes through the connecting pipe in sequence through the leading edge cavity, the third cooling channel, the leading edge bottom cavity, the fourth cooling channel, the transition cavity, the fifth cooling channel, the trailing edge bottom cavity, the sixth cooling channel, and the trailing edge cavity, and then returns to the cooling pipeline through the connecting pipe;

[0019] or;

[0020] The coolant passes through the connecting pipe in sequence through the trailing edge cavity, the sixth cooling channel, the trailing edge bottom cavity, the fifth cooling channel, the transition cavity, the fourth cooling channel, the leading edge bottom cavity, the third cooling channel, and the leading edge cavity, and then returns to the cooling pipe through the connecting pipe.

[0021] By adopting the above technical scheme, in the process of cooling the guide vane with coolant, the coolant can pass through the leading edge cavity, the third cooling channel, the leading edge bottom cavity, the fourth cooling channel, the transition cavity, the fifth cooling channel, the trailing edge bottom cavity, the sixth cooling channel, and the trailing edge cavity, thereby extending the time that the coolant stays in the guide vane, thereby facilitating the coolant to fully cool the guide vane.

[0022] Preferably, the thickness of the leading edge of the guide vane is greater than the thickness of the trailing edge, and the cooling cavity of the guide vane includes a leading edge cavity, a transition cavity, a trailing edge cavity, a leading edge bottom cavity and a trailing edge bottom cavity, the leading edge cavity is connected with the leading edge bottom cavity through a third cooling channel, the leading edge bottom cavity is connected with the transition cavity through a fourth cooling channel, the transition cavity is connected with the trailing edge bottom cavity through a fifth cooling channel, and the trailing edge bottom cavity is connected with the trailing edge cavity through a sixth cooling channel;

[0023] The method in which the coolant flows through the cooling cavity in the guide vane includes:

[0024] The coolant enters the leading edge cavity and the trailing edge cavity respectively through two connecting pipes. The coolant entering the leading edge cavity passes through the third cooling channel, the leading edge bottom cavity, the fourth cooling channel, and the transition cavity in sequence, and then returns to the cooling pipe through the connecting pipe; the coolant entering the trailing edge cavity passes through the sixth cooling channel, the trailing edge bottom cavity, the fifth cooling channel, and the transition cavity in sequence, and then returns to the cooling pipe through the connecting pipe.

[0025] By adopting the above technical scheme, in the process of hot air flowing through the guide blade, the leading edge of the guide blade contacts the hot air first relative to the trailing edge. At the same time, because the thickness of the leading edge of the guide blade is greater than the thickness of the trailing edge of the guide blade, the middle position of the guide blade can be in a lower temperature state relative to the leading and trailing edge positions of the guide blade. At this time, coolant flows from the transition cavity to the leading edge cavity or the trailing edge cavity, which facilitates cooling of the guide blade, so that the leading edge temperature and the trailing edge temperature on the guide blade are relatively close, and the temperature distribution on the guide blade is more uniform.

[0026] Preferably, the connecting device comprises a half clamping ring, a first guide block and a driving mechanism;

[0027] The guide blade is provided with a plug-in slot for the connecting pipe to be plugged in, the inner side wall of the plug-in slot is provided with a fixing slot, and the semi-clamping ring is slidably connected to the fixing slot;

[0028] The semi-clamping ring is provided with a limiting groove, the connecting pipe is fixedly connected with the limiting ring, and the limiting ring cooperates with the limiting groove;

[0029] The first guide block is fixedly connected to the half clamping ring, and a first guide groove for the first guide block to slide is provided on the inner side wall of the fixed groove;

[0030] The driving mechanism is used for driving the half clamping ring to move.

[0031] By adopting the above technical solution, after the connecting groove and the plug-in groove are plugged in, the semi-clamping ring is driven to move by the driving mechanism, so that the limiting ring and the limiting groove are plugged in and matched, thereby achieving the purpose of facilitating the fixing of the connecting pipe in the plug-in groove.

[0032] Preferably, the semi-clamping ring is provided with an inclined surface, and the inclined surface on the semi-clamping ring is arranged to be inclined downward from a side away from the connecting pipe to a side close to the connecting pipe.

[0033] By adopting the above technical solution, during the process of inserting the connecting pipe into the plug-in groove, the movement of the connecting pipe drives the movement of the limiting ring, and the movement of the limiting ring can conflict with the inclined surface of the semi-clamping ring, so that the limiting ring can push the semi-clamping ring to move, thereby facilitating the connection of the connecting pipe into the plug-in groove.

[0034] Preferably, the driving mechanism comprises a driving arc plate, a pushing gear and a second guide block;

[0035] The driving arc plate is slidably connected to the inner side wall of the fixing groove, the driving arc plate is away from the side of the connecting tube, the distance from one end of the driving arc plate to the other end from the axial center line of the connecting tube gradually decreases, and the side of the driving arc plate away from the connecting tube is fixedly connected with a rack;

[0036] The pushing gear is rotatably connected to the inner side wall of the fixing groove, and the pushing gear is meshed with the rack on the driving arc plate;

[0037] The second guide block is fixedly connected to the driving arc plate, and a second guide groove for the second guide block to slide is provided on the inner side wall of the fixed groove;

[0038] The driving mechanism also includes a rotating assembly for driving the pushing gear to rotate.

[0039] By adopting the above technical solution, in order to facilitate the driving of the semi-clamping ring to move, the driving gear is first driven to rotate through the rotating component, and the driving gear rotates to drive the driving arc plate to move. At this time, since the driving arc plate is away from one side of the connecting pipe, the distance from one end of the driving arc plate to the other end from the axial center line of the connecting pipe gradually decreases, so that during the movement of the driving arc plate, the semi-clamping ring can be pushed to move toward the side close to the connecting pipe.

[0040] Preferably, the rotating assembly comprises a driving gear and a gear ring, and the driving gear and the gear ring are both rotatably mounted on the inner side wall of the fixing groove;

[0041] The outer circumference and inner circumference of the gear ring are fixedly connected with gear teeth, and the driving gear is meshed with the gear teeth on the outer circumference of the gear ring; the pushing gear is meshed with the gear teeth on the inner circumference of the gear ring; and a driving component for driving the driving gear to rotate is also provided on the inner side wall of the fixed groove.

[0042] By adopting the above technical solution, in order to facilitate the rotation of the push gear, the driving assembly is first used to drive the driving gear to rotate, the driving gear rotates to drive the gear ring to rotate, and the gear ring rotates to drive the push gear to rotate, thereby achieving the purpose of facilitating the rotation of the push gear.

[0043] Preferably, a sliding hole is provided on the fixing groove, and the driving assembly comprises a screw rod and a pressing sleeve, and the screw rod is rotatably connected to the inner side wall of the fixing groove;

[0044] The screw is fixedly connected to the driving gear, the pressing sleeve is sleeved on the screw, and the screw is threadedly connected to the pressing sleeve; the pressing sleeve is slidably connected to the side wall of the sliding hole, and one end of the pressing sleeve protrudes from the guide blade setting.

[0045] By adopting the above technical solution, after the guide blade is installed in the worm gear brake by cold installation, as the temperature of the guide blade gradually rises, the shell of the worm gear brake can gradually push the pressing sleeve to move, and the movement of the pressing sleeve drives the screw to rotate, and the rotation of the screw drives the driving gear to rotate, thereby achieving the purpose of facilitating the rotation of the driving gear.

[0046] In summary, the present application includes at least one of the following beneficial technical effects:

[0047] In order to facilitate cooling of the guide vane, the electromagnetic pump is started to drive the cooling liquid in the cooling pipe to circulate, so that the cooling liquid flows into the cooling cavity of the guide vane through the connecting pipe, and then returns from the cooling cavity of the guide vane to the cooling pipe through the connecting pipe, thereby achieving the purpose of facilitating cooling of the guide vane;

[0048] In the process of cooling the guide vane with the coolant, the coolant can pass through the leading edge cavity, the first cooling channel, the bottom chamber, the second cooling channel, and the trailing edge cavity, so that the coolant can quickly pass through multiple parts of the guide vane, thereby facilitating the cooling of the guide vane;

[0049] In the process of cooling the guide vanes with coolant, the coolant can pass through the leading edge cavity, the third cooling channel, the leading edge bottom cavity, the fourth cooling channel, the transition cavity, the fifth cooling channel, the trailing edge bottom cavity, the sixth cooling channel, and the trailing edge cavity, thereby extending the time that the coolant stays in the guide vanes, thereby facilitating the coolant to fully cool the guide vanes.

[0050] When hot air flows through the guide vane, the leading edge of the guide vane contacts the hot air first relative to the trailing edge. At the same time, since the thickness of the leading edge of the guide vane is greater than the thickness of the trailing edge of the guide vane, the middle position of the guide vane can be in a lower temperature state relative to the leading and trailing edge positions of the guide vane. At this time, coolant flows from the transition cavity to the leading edge cavity or the trailing edge cavity to facilitate cooling of the guide vane, so that the leading edge temperature and the trailing edge temperature on the guide vane are relatively close, and the temperature distribution on the guide vane is more uniform. BRIEF DESCRIPTION OF THE DRAWINGS

[0051] Figure 1 It is a schematic diagram of the overall external structure of a guide blade in an embodiment of the present application.

[0052] Figure 2 It is a schematic diagram of the internal structure of a guide blade in Example 1 of the present application.

[0053] Figure 3 It is a schematic diagram of the internal structure of a guide blade in Example 2 of the present application.

[0054] Figure 4 This is a schematic diagram of the internal structure of a guide blade in Example 3 of the present application.

[0055] Figure 5 It is a cross-sectional view of the guide vane in the implementation of this application.

[0056] Figure 6 It is a schematic diagram of the exploded structure of the semi-clamping ring and the connecting pipe in the embodiment of the present application.

[0057] Figure 7 It is a structural schematic diagram highlighting the connection device in the embodiment of the present application.

[0058] Explanation of the accompanying drawings: 1. guide vane; 11. first cooling channel; 12. second cooling channel; 13. third cooling channel; 14. fourth cooling channel; 15. fifth cooling channel; 16. sixth cooling channel; 17. fixing groove; 171. sliding hole; 18. first guide groove; 19. plug-in groove; 2. cooling cavity; 21. leading edge cavity; 22. trailing edge cavity; 23. bottom cavity; 24. transition cavity; 25. leading edge bottom cavity; 26. trailing edge bottom cavity; 3. connecting pipe; 31. limiting ring; 4. semi-clamping ring; 41. limiting groove; 42. first guide block; 5. driving mechanism; 51. driving arc plate; 52. pushing gear; 53. second guide block; 54. rotating assembly; 541. driving gear; 542; gear ring; 6. driving assembly; 61. screw; 62. pressing sleeve. DETAILED DESCRIPTION

[0059] The following is combined with Figure 1-7 The present application is further described in detail. The present application discloses a method for cooling the blades of a turbine guide vane of an aircraft engine. The method includes the following three implementation methods:

[0060] Embodiment 1:

[0061] Reference Figure 1 , Figure 2 as well as Figure 3 The method is applied to an aviation turbine guide vane 1, and the scheme comprises the following steps:

[0062] Step 1: Install cooling pipes, heat exchangers and electromagnetic pumps on the turbine brake of the aircraft engine, and add coolant to the cooling pipe, where the coolant is liquid metal. The heat exchanger and the electromagnetic pump are connected in series in the cooling pipe. A cooling cavity 2 is provided inside the guide vane 1, and two connecting pipes 3 are installed on the cooling pipe corresponding to each guide vane 1. The coolant in the cooling pipe can enter the cooling cavity 2 of the guide vane 1 through one of the connecting pipes 3, and then flow back to the cooling pipe through the other connecting pipe 3.

[0063] Step 2: Start the electromagnetic pump so that the coolant flows into the cooling cavity 2 of the guide vane 1 through the connecting pipe 3, and then the coolant returns from the cooling cavity 2 in the guide vane 1 through another connecting pipe 3 to the cooling pipe.

[0064] The two ends of the guide vane 1 may be respectively referred to as the leading edge and the trailing edge, and the thickness of the leading edge of the guide vane 1 is greater than the thickness of the trailing edge.

[0065] like Figure 1 and Figure 2As shown, the cooling cavity 2 of the guide vane 1 includes a leading edge cavity 21, a trailing edge cavity 22 and a bottom cavity 23. A plurality of first cooling channels 11 and a plurality of second cooling channels 12 are also provided in the guide vane 1. The leading edge cavity 21 is connected to the bottom cavity 23 through the first cooling channel 11, and the bottom cavity 23 is connected to the trailing edge cavity 22 through the second cooling channel 12.

[0066] In the process of the coolant passing into the guide vane 1 through the connecting pipe 3, the coolant can pass through the leading edge cavity 21, the first cooling channel 11, the bottom chamber 23, the second cooling channel 12, and the trailing edge cavity 22 in sequence, and then return to the cooling pipe through the connecting pipe 3; or; pass through the trailing edge cavity 22, the second cooling channel 12, the bottom chamber 23, the first cooling channel 11, and the leading edge cavity 21 in sequence, and then return to the cooling pipe through the connecting pipe 3.

[0067] In the process of cooling the guide vane 1 by using the coolant, the coolant can quickly pass through multiple locations in the guide vane 1, thereby facilitating cooling of the guide vane 1.

[0068] Embodiment 2:

[0069] like Figure 3 As shown, the difference between the second embodiment and the first embodiment is only in the cooling cavity 2 and the way in which the coolant flows through the guide vane 1, wherein the cooling cavity 2 of the guide vane 1 includes a leading edge cavity 21, a transition cavity 24, a trailing edge cavity 22, a leading edge bottom cavity 25 and a trailing edge bottom cavity 26, and the guide vane 1 is also provided with a plurality of third cooling channels 13, a plurality of fourth cooling channels 14, a plurality of fifth cooling channels 15 and a plurality of sixth cooling channels 16.

[0070] The leading edge cavity 21 is connected to the leading edge bottom cavity 25 through the third cooling channel 13, the leading edge bottom cavity 25 is connected to the transition cavity 24 through the fourth cooling channel 14, the transition cavity 24 is connected to the trailing edge bottom cavity 26 through the fifth cooling channel 15, and the trailing edge bottom cavity 26 is connected to the trailing edge cavity 22 through the sixth cooling channel 16;

[0071] In the process of coolant passing into the guide vane 1 through the connecting pipe 3, the coolant can sequentially pass through the leading edge cavity 21, the third cooling channel 13, the leading edge bottom cavity 25, the fourth cooling channel 14, the transition cavity 24, the fifth cooling channel 15, the trailing edge bottom cavity 26, the sixth cooling channel 16, and the trailing edge cavity 22, and then return to the cooling pipeline through the connecting pipe 3; or; the coolant can sequentially pass through the trailing edge cavity 22, the sixth cooling channel 16, the trailing edge bottom cavity 26, the fifth cooling channel 15, the transition cavity 24, the fourth cooling channel 14, the leading edge bottom cavity 25, the third cooling channel 13, and the leading edge cavity 21, and then return to the cooling pipeline through the connecting pipe 3. Thereby, the retention time of the coolant in the guide vane 1 is prolonged, and it is convenient for the coolant to fully cool the guide vane 1.

[0072] Implementation three:

[0073] Figure 4 As shown, the difference between the third embodiment and the second embodiment is only the connection method between the guide vane 1 and the cooling pipe, and the way the coolant flows through the guide vane 1, wherein the cooling pipe is connected to the guide vane 1 through three connecting pipes 3, and the three connecting pipes 3 are respectively connected to the leading edge cavity 21, the transition cavity 24 and the trailing edge cavity 22.

[0074] The coolant enters the leading edge cavity 21 and the trailing edge cavity 22 respectively through the two connecting pipes 3. The coolant entering the leading edge cavity 21 passes through the third cooling channel 13, the leading edge bottom cavity 25, the fourth cooling channel 14, and the transition cavity 24 in sequence, and then returns to the cooling pipe through the connecting pipe 3; the coolant entering the trailing edge cavity 22 passes through the sixth cooling channel 16, the trailing edge bottom cavity 26, the fifth cooling channel 15, and the transition cavity 24 in sequence, and then returns to the cooling pipe through the connecting pipe 3.

[0075] When hot air flows through the guide vane 1, the leading edge of the guide vane 1 contacts the hot air first relative to the trailing edge. At the same time, since the thickness of the leading edge of the guide vane 1 is greater than the thickness of the trailing edge of the guide vane 1, the middle position of the guide vane 1 is relatively slower than the leading and trailing edge positions of the guide vane 1, so that the middle of the guide vane 1 can heat up more slowly. By introducing coolant into the guide leading edge cavity 21 and the trailing edge cavity 22, the guide leading edge cavity 21 and the trailing edge cavity 22 can be cooled preferentially, so that the temperature distribution on the guide vane 1 is more uniform.

[0076] The present application also discloses a connecting device for guide vanes, such as Figure 1 and Figure 4 As shown, the connecting device is used to connect the connecting pipe 3 to the guide vane 1. The guide vane 1 is provided with an inserting groove 19 for the connecting pipe 3 to be inserted into. The inner wall of the inserting groove 19 is provided with a fixing groove 17.

[0077] like Figure 5 and Figure 6 As shown, the connection device includes two half clamping rings 4, two first guide blocks 42 and a driving mechanism 5. The two half clamping rings 4 are slidably connected to the inner side wall of the fixing groove 17. The two half clamping rings 4 can form a complete ring after being spliced ​​together, and the two half clamping rings 4 are used to fix the connecting pipe 3 after being spliced ​​together. The two half clamping rings 4 are provided with limiting grooves 41, and the limiting rings 31 are fixedly connected to the connecting pipe 3, and the limiting rings 31 are plugged and matched with the two limiting grooves 41 at the same time.

[0078] The two half clamping rings 4 are provided with inclined surfaces on the sides close to each other, and the inclined surfaces of the two half clamping rings 4 are inclined downward from the side away from the connecting pipe 3 to the side close to the connecting pipe 3, so that the limiting ring 31 can push the two half clamping rings 4 to move to the side away from each other, thereby facilitating the connection pipe 3 to be inserted into the insertion groove 19.

[0079] like Figure 5 and Figure 7 As shown, two first guide blocks 42 are fixedly connected to the two half clamping rings 4 in a one-to-one correspondence, two first guide grooves 18 are provided in the fixed groove 17, and the two first guide blocks 42 are slidably connected to the inner side walls of the two first guide grooves 18 in a one-to-one correspondence. The driving mechanism 5 is used to drive the two half clamping rings 4 to move toward the side close to the axis of the connecting pipe 3.

[0080] like Figure 5 , Figure 6 as well as Figure 7 As shown, the driving mechanism 5 includes two driving arc plates 51, two pushing gears 52, two second guide blocks 53 and a rotating assembly 54. The two driving arc plates 51 are both slidably connected to the inner wall of the fixing groove 17, and the relative inner sides of the two driving arc plates 51 are in one-to-one contact with the relative outer sides of the two half clamping rings 4. Among them, a rack is fixedly connected to the side of the driving arc plate 51 away from the connecting pipe 3, and the distance from the axial center line of the connecting pipe 3 to the driving arc plate 51 from one end to the other end gradually decreases.

[0081] The two push gears 52 are both rotatably connected to the inner side wall of the fixed groove 17, and the two push gears 52 are meshed with the racks of the two driving arc plates 51 in a one-to-one correspondence. The two second guide blocks 53 are fixedly connected to the two driving arc plates 51 in a one-to-one correspondence, and two second guide grooves for the two second guide blocks 53 to slide are provided in the fixed groove 17, and in order to reduce the friction between the second guide blocks 53 and the second guide grooves, rollers or wheels can be installed on the second guide blocks 53.

[0082] like Figure 5 , Figure 6 as well as Figure 7As shown, the rotating assembly 54 includes a driving gear 541 and a gear ring 542, and the driving gear 541 and the gear ring 542 are both rotatably connected to the inner wall of the fixing groove 17, and gear teeth are fixedly connected to the inner and outer surfaces of the gear ring 542, and the gear teeth on the inner surface of the gear ring 542 are meshed with the two pushing gears 52 at the same time, and the gear teeth on the outer surface of the gear ring 542 are meshed with the driving gear 541.

[0083] The guide blade 1 is also provided with a driving assembly 6 for rotating the driving gear 541. The driving assembly 6 includes a screw 61 and a pressing sleeve 62. The screw 61 is rotatably connected to the inner wall of the fixing groove 17, and the screw 61 is fixedly connected to the driving gear 541. A sliding hole 171 is provided on the inner wall of the fixing groove 17, and a portion of the pressing sleeve 62 passes through the sliding hole 171 and protrudes out of the guide blade 1. The pressing sleeve 62 is slidably connected to the inner wall of the sliding hole 171, and the pressing sleeve 62 is sleeved on the screw 61, and the pressing sleeve 62 is threadedly connected to the screw 61.

[0084] like Figure 5 and Figure 6 As shown, in the process of installing the guide vane 1 on the turbine gate of the aircraft engine by cold installation, as the temperature on the guide vane 1 rises, the pressing sleeve 62 is gradually able to abut against the turbine gate and push the pressing sleeve 62 to move. The movement of the pressing sleeve 62 drives the screw 61 to rotate, and the rotation of the screw 61 drives the driving gear 541 to rotate. The driving gear 541 rotates to drive the gear 541 ring to rotate, and the gear ring 542 rotates to drive the two pushing gears 52 to rotate. The two pushing gears 52 rotate to drive the two driving arc plates 51 to move.

[0085] During the movement of the two driving arc plates 51, the two half clamping rings 4 can be pushed to move due to the shape of the two driving arc plates 51, so that the two half clamping rings 4 move toward each other; when the limiting grooves 41 of the two half clamping rings 4 cooperate with the limiting rings 31 on the connecting pipe 3, the two half clamping rings 4 clamp the connecting pipe 3, thereby achieving the purpose of fixing the connecting pipe 3.

[0086] The above are all preferred embodiments of the present application, and the protection scope of the present application is not limited thereto. Therefore, any equivalent changes made according to the structure, shape, and principle of the present application should be included in the protection scope of the present application.

Claims

1. A method for cooling an aircraft engine turbine guide vane, characterized in that: The method is applied to a guide vane (1) of an aircraft engine, wherein the guide vane (1) is provided with a cooling cavity (2), and the method comprises: A cooling pipeline, a heat exchanger and an electromagnetic pump are installed on the turbine brake of an aircraft engine, and coolant is added to the cooling pipeline, wherein the heat exchanger and the electromagnetic pump are connected in series to the cooling pipeline, and the cooling cavity (2) in the guide vane (1) is connected to the cooling pipeline through more than two connecting pipes (3) installed on the cooling pipeline; Starting the electromagnetic pump so that the coolant flows from the cooling pipeline through the connecting pipe (3) into the cooling cavity (2) of the guide vane (1), and then the coolant returns from the cooling cavity (2) in the guide vane (1) through another connecting pipe (3) to the cooling pipeline; The thickness of the leading edge of the guide vane (1) is greater than the thickness of the trailing edge, and the cooling cavity (2) of the guide vane (1) comprises a leading edge cavity (21), a transition cavity (24), a trailing edge cavity (22), a leading edge bottom cavity (25) and a trailing edge bottom cavity (26), the leading edge cavity (21) and the leading edge bottom cavity (25) are connected via a third cooling channel (13), the leading edge bottom cavity (25) and the transition cavity (24) are connected via a fourth cooling channel (14), the transition cavity (24) and the trailing edge bottom cavity (26) are connected via a fifth cooling channel (15), and the trailing edge bottom cavity (26) and the trailing edge cavity (22) are connected via a sixth cooling channel (16); The cooling pipeline is connected to the guide vane (1) via three connecting pipes (3), and the three connecting pipes (3) are respectively connected to the leading edge cavity (21), the transition cavity (24) and the trailing edge cavity (22); The method in which the coolant flows through the cooling cavity (2) in the guide vane (1) includes: The cooling liquid respectively enters the leading edge cavity (21) and the trailing edge cavity (22) through the two connecting pipes (3); the cooling liquid entering the leading edge cavity (21) passes through the third cooling channel (13), the leading edge bottom cavity (25), the fourth cooling channel (14), and the transition cavity (24) in sequence, and then returns to the cooling pipeline through the connecting pipe (3); the cooling liquid entering the trailing edge cavity (22) passes through the sixth cooling channel (16), the trailing edge bottom cavity (26), the fifth cooling channel (15), and the transition cavity (24) in sequence, and then returns to the cooling pipeline through the connecting pipe (3).

2. A connecting device for a guide vane, according to the cooling method of an aircraft engine turbine guide vane according to claim 1, characterized in that: The connecting device comprises a half clamping ring (4), a first guide block (42) and a driving mechanism (5); The guide blade (1) is provided with a plug-in slot (19) for the connecting pipe (3) to be plugged in, the inner side wall of the plug-in slot (19) is provided with a fixing slot (17), and the semi-clamping ring (4) is slidably connected to the fixing slot (17); The semi-clamping ring (4) is provided with a limiting groove (41), the connecting pipe (3) is fixedly connected with a limiting ring (31), and the limiting ring (31) matches the limiting groove (41); The first guide block (42) is fixedly connected to the half clamping ring (4), and a first guide groove (18) for the first guide block (42) to slide is provided on the inner side wall of the fixed groove (17); The driving mechanism (5) is used to drive the semi-clamping ring (4) to move; The driving mechanism (5) comprises a driving arc plate (51), a pushing gear (52) and a second guide block (53); The driving arc plate (51) is slidably connected to the inner side wall of the fixing groove (17); the driving arc plate (51) is away from the side of the connecting tube (3); the distance from one end of the driving arc plate (51) to the other end of the driving arc plate (51) from the axial center line of the connecting tube (3) gradually decreases; and the side of the driving arc plate (51) away from the connecting tube (3) is fixedly connected with a rack; The pushing gear (52) is rotatably connected to the inner side wall of the fixing groove (17), and the pushing gear (52) is meshed with the rack on the driving arc plate (51); The second guide block (53) is fixedly connected to the driving arc plate (51), and a second guide groove for the second guide block (53) to slide is provided on the inner side wall of the fixed groove (17); The driving mechanism (5) also includes a rotating assembly (54) for driving the pushing gear (52) to rotate.

3. A connecting device for a guide vane (1) according to claim 2, characterized in that: The semi-clamping ring (4) is provided with an inclined surface, and the inclined surface on the semi-clamping ring (4) is arranged to be inclined downward from a side away from the connecting pipe (3) to a side close to the connecting pipe (3).

4. The connecting device for the guide vane (1) according to claim 2, characterized in that: The rotating assembly (54) comprises a driving gear (541) and a gear ring (542), and the driving gear (541) and the gear ring (542) are both rotatably mounted on the inner side wall of the fixing groove (17); The outer circumference and inner circumference of the gear ring (542) are both fixedly connected with gear teeth; the driving gear (541) meshes with the gear teeth on the outer circumference of the gear ring (542); the pushing gear (52) meshes with the gear teeth on the inner circumference of the gear ring (542); and a driving component (6) for driving the driving gear (541) to rotate is also provided on the inner side wall of the fixing groove (17).

5. The connecting device for the guide vane (1) according to claim 4, characterized in that: The fixing groove (17) is provided with a sliding hole (171), the driving assembly (6) comprises a screw rod (61) and a pressing sleeve (62), and the screw rod (61) is rotatably connected to the inner side wall of the fixing groove (17); The screw rod (61) is fixedly connected to the driving gear (541), the pressing sleeve (62) is sleeved on the screw rod (61), and the screw rod (61) and the pressing sleeve (62) are threadedly connected; the pressing sleeve (62) is slidably connected to the side wall of the sliding hole (171), and one end of the pressing sleeve (62) protrudes from the guide blade (1).

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