CN115522987A

CN115522987A - Method for cooling blades of turbine guide device of aircraft engine

Info

Publication number: CN115522987A
Application number: CN202211222612.6A
Authority: CN
Inventors: 罗翔; 王嗣鹏; 张哲�; 刘冬冬; 邬泽宇
Original assignee: Beihang University
Current assignee: Beihang University
Priority date: 2022-10-08
Filing date: 2022-10-08
Publication date: 2022-12-27

Abstract

The application discloses a method for cooling a blade of a turbine guider of an aero-engine, which belongs to the technical field of aero-engine cooling, and is applied to the blade of the guider of the aero-engine, wherein the blade of the guider is provided with a cooling cavity; installing a cooling pipeline, a heat exchanger and an electromagnetic pump on a turbine gate of an aircraft engine, and adding cooling liquid into the cooling pipeline, wherein the heat exchanger and the electromagnetic pump are connected in series in the cooling pipeline, and a cooling cavity in a guide vane is communicated with the cooling pipeline through more than two connecting pipes arranged on the cooling pipeline; the electromagnetic pump is started, so that the cooling liquid flows into the cooling cavity of the guide vane through the connecting pipe from the cooling pipeline, and then the cooling liquid returns to the cooling pipeline through another connecting pipe from the cooling cavity in the guide vane. This application is through starting electromagnetic pump for during cooling liquid flowed in the cooling chamber of director blade through the connecting pipe, reach and be convenient for carry out refrigerated purpose to the director blade.

Description

Method for cooling blades of turbine guide device of aircraft engine

Technical Field

The application relates to the technical field of aircraft engine cooling, in particular to a method for cooling blades of a turbine guider of an aircraft engine.

Background

With the continuous development of the modern aviation industry, the aero-engine develops towards the direction of high thrust-weight ratio, high efficiency, high reliability and low oil consumption, and the thrust-weight ratio can be effectively increased by increasing the temperature of the turbine inlet. At the same time, as the turbine inlet temperature increases, far beyond the refractory temperature of the turbine material, the nozzle vane temperature in the turbine gate must be cooled to a lower range using nozzle vane cooling techniques.

At present, in the cooling mode of a hot end part of an aircraft engine, cold air enters the interior of the aircraft engine through a secondary air system, air is introduced into the interior of the aircraft engine and then enters from a drum hole of a compressor, flows into an axis channel through a disc cavity of the compressor rotating at a high speed, and finally flows through a turbine disc cavity and a guide vane. By means of such bleed air, a series of pressure losses occur, with a corresponding increase in the temperature of the cold air, and the more complex the structure of the guide vane brings about an increase in the production costs.

Disclosure of Invention

In order to facilitate cooling of the nozzle blades, the present application provides a method of cooling aircraft engine turbine nozzle blades.

The application provides an aeroengine turbine guider blade cooling method adopts the following technical scheme:

a method for cooling a turbine guider blade of an aeroengine is applied to the guider blade of the aeroengine, and the guider blade is provided with a cooling cavity;

installing a cooling pipeline, a heat exchanger and an electromagnetic pump on a turbine gate of an aircraft engine, and adding cooling liquid into the cooling pipeline, wherein the heat exchanger and the electromagnetic pump are connected in series in the cooling pipeline, and a cooling cavity in the guide vane is communicated with the cooling pipeline through more than two connecting pipes arranged on the cooling pipeline;

and starting the electromagnetic pump, so that the cooling liquid flows into the cooling cavity of the guide vane from the cooling pipeline through the connecting pipe, and then the cooling liquid returns to the cooling pipeline from the cooling cavity in the guide vane through another connecting pipe.

Through adopting above-mentioned technical scheme, in order to facilitate cooling down the director blade, through starting the electromagnetic pump for the electromagnetic pump orders about the cooling liquid circulation in the cooling duct, thereby makes during cooling liquid flows into the cooling chamber of director blade through the connecting pipe, then returns to the cooling duct by the cooling chamber of director blade through the connecting pipe again, thereby reaches and is convenient for carry out refrigerated purpose to the director blade.

Preferably, the thickness of the leading edge of the guide vane is greater than that of the trailing edge, the cooling cavity of the guide vane comprises a leading edge cavity, a trailing edge cavity and a bottom cavity, the leading edge cavity is communicated with the bottom cavity through a first cooling channel, and the bottom cavity is communicated with the trailing edge cavity through a second cooling channel;

the manner in which the cooling fluid flows through the cooling cavity in the nozzle vane includes:

the cooling liquid sequentially passes through the front edge cavity, the first cooling channel, the bottom cavity, the second cooling channel and the rear edge cavity through the connecting pipe and then returns to the cooling pipeline through the connecting pipe;

or;

the cooling liquid sequentially passes through the rear edge cavity, the second cooling channel, the bottom cavity, the first cooling channel and the front edge cavity through the connecting pipes and then returns to the cooling pipeline through the connecting pipes.

Through adopting above-mentioned technical scheme, utilizing the coolant liquid to carry out the in-process that cools off to the director blade, the coolant liquid can be through leading edge chamber, first cooling channel, bottom cavity, second cooling channel, trailing edge chamber to the coolant liquid can be fast through a plurality of positions in the director blade, thereby is convenient for play the effect of cooling the director blade.

Preferably, the thickness of the leading edge of the guide vane is greater than that of the trailing edge, the cooling cavity of the guide vane comprises 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 communicated with the leading edge bottom cavity through a third cooling channel, the leading edge bottom cavity is communicated with the transition cavity through a fourth cooling channel, the transition cavity is communicated with the trailing edge bottom cavity through a fifth cooling channel, and the trailing edge bottom cavity is communicated with the trailing edge cavity through a sixth cooling channel;

the cooling liquid sequentially passes through the front edge cavity, the third cooling channel, the front edge bottom cavity, the fourth cooling channel, the transition cavity, the fifth cooling channel, the rear edge bottom cavity, the sixth cooling channel and the rear edge cavity through the connecting pipes and then returns to the cooling pipeline through the connecting pipes;

or;

the cooling liquid sequentially passes through the rear edge cavity, the sixth cooling channel, the rear edge bottom cavity, the fifth cooling channel, the transition cavity, the fourth cooling channel, the front edge bottom cavity, the third cooling channel and the front edge cavity through the connecting pipes and then returns to the cooling pipeline through the connecting pipes.

By adopting the technical scheme, in the process of cooling the guider blade by using the cooling liquid, the cooling liquid can pass through the front edge cavity, the third cooling channel, the front edge bottom cavity, the fourth cooling channel, the transition cavity, the fifth cooling channel, the rear edge bottom cavity, the sixth cooling channel and the rear edge cavity, so that the time length of the cooling liquid staying in the guider blade is prolonged, and the guider blade can be sufficiently cooled by the cooling liquid.

the cooling liquid respectively enters the front edge cavity and the rear edge cavity through two connecting pipes, and the cooling liquid entering the front edge cavity sequentially passes through the third cooling channel, the front edge bottom cavity, the fourth cooling channel and the transition cavity and then returns to the cooling pipeline through the connecting pipes; and the cooling liquid entering the rear edge cavity sequentially passes through the sixth cooling channel, the rear edge bottom cavity, the fifth cooling channel and the transition cavity and then returns to the cooling pipeline through the connecting pipe.

By adopting the technical scheme, in the process that hot air flows through the guide vane, the front edge of the guide vane is contacted with the hot air relative to the tail edge, and simultaneously, as the thickness of the front edge of the guide vane is greater than that of the tail edge of the guide vane, the middle position of the guide vane can be in a low-temperature state relative to the front edge and the tail edge of the guide vane; at the moment, the cooling liquid circulates from the transition cavity to the front edge cavity or the rear edge cavity, so that the temperature of the guide vane is conveniently reduced, the temperature of the front edge and the temperature of the rear edge of the guide vane are relatively close, and the temperature distribution on the guide vane is relatively uniform.

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

the guide vane is provided with an inserting groove for inserting the connecting pipe, the inner side wall of the inserting groove is provided with a fixed groove, and the semi-clamping ring is connected with the fixed groove in a sliding manner;

the semi-clamping ring is provided with a limiting groove, the connecting pipe is fixedly connected with a limiting ring, and the limiting ring is matched with the limiting groove;

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 formed in the inner side wall of the fixing groove;

the driving mechanism is used for driving the half clamping ring to move.

Through adopting above-mentioned technical scheme, after spread groove and inserting groove are pegged graft and are cooperated, remove through half grip ring of actuating mechanism drive to make spacing ring and spacing groove peg graft and cooperate, and then reach and be convenient for be fixed in the purpose of inserting groove with the connecting pipe.

Preferably, the half clamping ring is provided with an inclined surface, and the inclined surface on the half clamping ring is inclined downwards from the side far away from the connecting pipe to the side close to the connecting pipe.

Through adopting above-mentioned technical scheme, at the in-process of connecting pipe grafting inserting groove, the connecting pipe removes and drives the spacing ring and remove, and the spacing ring removes and can inconsistent with the inclined plane of half grip ring to make the spacing ring can promote half grip ring and remove, and then be convenient for the connecting pipe to peg graft in the inserting groove.

Preferably, the driving mechanism comprises a driving arc-shaped plate, a pushing gear and a second guide block;

the driving arc plate is connected with the inner side wall of the fixing groove in a sliding mode, one side, away from the connecting pipe, of the driving arc plate is gradually reduced in distance from the axial lead of the connecting pipe from one end to the other end of the driving arc plate, and a rack is fixedly connected to one side, away from the connecting pipe, of the driving arc plate;

the pushing gear is rotatably connected with the inner side wall of the fixing groove and meshed with the rack on the driving arc-shaped plate;

the second guide block is fixedly connected to the driving arc-shaped plate, and a second guide groove for the second guide block to slide is formed in the inner side wall of the fixing groove;

the driving mechanism also comprises a rotating component for driving the pushing gear to rotate.

Through adopting above-mentioned technical scheme, for the ease of driving half centre gripping ring and removing, promote gear revolve through the runner assembly drive earlier, promote gear revolve drive arc and remove, at this moment, because the drive arc is kept away from one side of connecting pipe, from drive arc wherein one end to the distance of another end apart from the connecting pipe axial lead reduces gradually to make the drive arc remove the in-process, can promote half centre gripping ring to the one side that is close to the connecting pipe and remove.

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

the outer circumferential surface and the inner circumferential surface of the gear ring are fixedly connected with gear teeth, and the driving gear is meshed with the gear teeth on the outer circumferential surface of the gear ring; the pushing gear is meshed with gear teeth on the inner circumferential surface of the gear ring; and a driving assembly for driving the driving gear to rotate is further arranged on the inner side wall of the fixing groove.

Through adopting above-mentioned technical scheme, for the ease of promoting the gear rotation, earlier rotate through drive assembly drive gear, drive gear rotates drive gear ring and rotates, and gear ring rotation drive promotes the gear rotation to reach the drive of being convenient for and promote gear pivoted purpose.

Preferably, a sliding hole is formed in the fixing groove, the driving assembly comprises a screw and a pressing sleeve, and the screw is rotationally connected with the inner side wall of the fixing groove;

the screw rod is fixedly connected with the driving gear, the pressing sleeve is sleeved on the screw rod, and the screw rod is in threaded connection with the pressing sleeve; the pressing sleeve is connected with the side wall of the sliding hole in a sliding mode, and one end of the pressing sleeve protrudes out of the guide vane.

Through adopting above-mentioned technical scheme, through the mode of cold installation, after installing the director blade in worm gear floodgate, at the in-process that the temperature of director blade rises gradually, the casing of worm gear floodgate can promote gradually and press the sleeve and remove, presses down the sleeve and removes and orders about the screw rod and rotate, and the screw rod rotates and drives drive gear and rotate to reach and be convenient for make drive gear pivoted purpose.

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

in order to facilitate cooling of the guide vane, the electromagnetic pump is started to drive cooling liquid in the cooling pipeline to circulate, so that the cooling liquid flows into the cooling cavity of the guide vane through the connecting pipe and then returns to the cooling pipeline through the connecting pipe from the cooling cavity of the guide vane, and therefore the purpose of facilitating cooling of the guide vane is achieved;

in the process of cooling the guide vane by using the cooling liquid, the cooling liquid can pass through the front edge cavity, the first cooling channel, the bottom cavity, the second cooling channel and the rear edge cavity, so that the cooling liquid can quickly pass through a plurality of parts in the guide vane, and the guide vane is convenient to cool;

in the process of cooling the guide vane by using the cooling liquid, the cooling liquid can pass through the front edge cavity, the third cooling channel, the front edge bottom cavity, the fourth cooling channel, the transition cavity, the fifth cooling channel, the rear edge bottom cavity, the sixth cooling channel and the rear edge cavity, so that the time length of the cooling liquid staying in the guide vane is prolonged, and the guide vane can be sufficiently cooled by the cooling liquid.

In the process that hot air flows through the guide vane, the front edge of the guide vane is firstly contacted with the hot air relative to the tail edge, and simultaneously, the thickness of the front edge of the guide vane is larger than that of the tail edge of the guide vane, so that the middle position of the guide vane can be in a lower temperature state relative to the front edge and the tail edge of the guide vane; at the moment, the cooling liquid circulates from the transition cavity to the front edge cavity or the rear edge cavity, so that the temperature of the guide vane is conveniently reduced, the temperature of the front edge and the temperature of the rear edge of the guide vane are relatively close, and the temperature distribution on the guide vane is relatively uniform.

Drawings

FIG. 1 is a schematic view of the overall external structure of a vane of one of the embodiments of the present application.

Fig. 2 is a schematic view of an internal structure of a vane of an embodiment of the present application.

Fig. 3 is a schematic view of an internal structure of a vane of a second embodiment of the present application.

Fig. 4 is a schematic internal structural view of a vane of a third embodiment of the present application.

FIG. 5 is a cross-sectional view of a vane of the vane in the practice of the present application.

Fig. 6 is an exploded view of the half clamp ring and the connecting tube in the embodiment of the present application.

FIG. 7 is a schematic view showing the structure of the connection device in the embodiment of the present application.

Description of reference numerals: 1. a guide vane; 11. a first cooling channel; 12. a second cooling channel; 13. a third cooling channel; 14. a fourth cooling channel; 15. a fifth cooling channel; 16. a sixth cooling channel; 17. fixing grooves; 171. a sliding hole; 18. a first guide groove; 19. inserting grooves; 2. a cooling chamber; 21. a leading edge cavity; 22. a trailing edge cavity; 23. a bottom chamber; 24. a transition chamber; 25. a leading edge bottom cavity; 26. a trailing edge bottom cavity; 3. a connecting pipe; 31. a limiting ring; 4. a half clamp ring; 41. a limiting groove; 42. a first guide block; 5. a drive mechanism; 51. driving the arc-shaped plate; 52. a push gear; 53. a second guide block; 54. a rotating assembly; 541. a drive gear; 542; a gear ring; 6. a drive assembly; 61. a screw; 62. the sleeve is pressed.

Detailed Description

The present application is described in further detail below with reference to figures 1-7. The application discloses a method for cooling blades of a turbine guider of an aircraft engine. The method comprises the following three embodiments:

the first embodiment is as follows:

with reference to fig. 1, 2 and 3, the method is applied in an aeronautical turbine guide vane 1, the solution comprising the following steps:

the method comprises the following steps: installing a cooling pipeline, a heat exchanger and an electromagnetic pump on a turbine gate of an aircraft engine, and adding cooling liquid into the cooling pipeline, wherein the cooling liquid is liquid metal. Wherein, heat exchanger and electromagnetic pump all establish ties in the cooling duct. Cooling chamber 2 has been seted up to the inside of director blade 1, and corresponds every director blade 1 and install two connecting pipes 3 on the cooling tube, and the coolant liquid in the cooling tube can get into in the cooling chamber 2 of director blade 1 through one of them connecting pipe 3, then flows back to the cooling tube in by another connecting pipe 3.

Step two: the electromagnetic pump is started so that the cooling liquid flows into the cooling chamber 2 of the guide vane 1 through the connecting pipe 3, and then the cooling liquid is returned to the cooling pipe through the other connecting pipe 3 from the cooling chamber 2 in the guide vane 1.

Both ends of the guide vane 1 may be referred to as a leading edge and a trailing edge, respectively, and the thickness of the leading edge of the guide vane 1 is greater than that of the trailing edge.

As shown in fig. 1 and fig. 2, 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, the guide vane 1 further has a plurality of first cooling channels 11 and a plurality of second cooling channels 12, the leading edge cavity 21 is communicated with the bottom cavity 23 through the first cooling channels 11, and the bottom cavity 23 is communicated with the trailing edge cavity 22 through the second cooling channels 12.

In the process that the cooling liquid is introduced into the guide vane 1 through the connecting pipe 3, the cooling liquid can pass through the front edge cavity 21, the first cooling channel 11, the bottom cavity 23, the second cooling channel 12 and the rear edge cavity 22 in sequence and then return to the cooling pipeline through the connecting pipe 3; or; the cooling medium passes through the trailing edge cavity 22, the second cooling channel 12, the bottom cavity 23, the first cooling channel 11, and the leading edge cavity 21 in this order, and then returns to the cooling duct through the connection pipe 3.

In the process of cooling the guide vane 1 by using the cooling liquid, the cooling liquid can rapidly pass through a plurality of positions in the guide vane 1, thereby facilitating the cooling of the guide vane 1.

The second embodiment:

as shown in fig. 3, the second embodiment is different from the first embodiment only in the manner that the cooling cavity 2 and the cooling liquid flow 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 further 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.

The front edge cavity 21 is communicated with the front edge bottom cavity 25 through a third cooling channel 13, the front edge bottom cavity 25 is communicated with the transition cavity 24 through a fourth cooling channel 14, the transition cavity 24 is communicated with the rear edge bottom cavity 26 through a fifth cooling channel 15, and the rear edge bottom cavity 26 is communicated with the rear edge cavity 22 through a sixth cooling channel 16;

in the process that the cooling liquid is introduced into the guide vane 1 through the connecting pipe 3, the cooling liquid can pass through the front edge cavity 21, the third cooling channel 13, the front edge bottom cavity 25, the fourth cooling channel 14, the transition cavity 24, the fifth cooling channel 15, the rear edge bottom cavity 26, the sixth cooling channel 16 and the rear edge cavity 22 in sequence 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 extending the time period that the coolant stays in the guide vane 1, and further facilitating the coolant to sufficiently cool the guide vane 1.

And (3) implementation:

fig. 4 shows that the third embodiment differs from the second embodiment only in the way in which the guide vane 1 is connected to the cooling duct and in the way in which the cooling liquid flows through the guide vane 1, wherein the cooling duct is connected to the guide vane 1 by three connecting pipes 3, and the three connecting pipes 3 are respectively in communication with the leading edge chamber 21, the transition chamber 24 and the trailing edge chamber 22.

The cooling liquid respectively enters the front edge cavity 21 and the rear edge cavity 22 through the two connecting pipes 3, and the cooling liquid entering the front edge cavity 21 passes through the third cooling channel 13, the front 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 pipes 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.

In the process that hot air flows through the guide vane 1, the front edge of the guide vane 1 is firstly contacted with the hot air relative to the tail edge, and meanwhile, the thickness of the front edge of the guide vane 1 is larger than that of the tail edge of the guide vane 1, so that the middle position of the guide vane 1 is relative to the front edge and the tail edge of the guide vane 1, and the temperature rise in the middle of the guide vane 1 can be slower. By means of the coolant entering the leading edge cavity 21 and the trailing edge cavity 22 of the guide vane, the leading edge cavity 21 and the trailing edge cavity 22 of the guide vane can be cooled preferentially, so that the temperature distribution on the guide vane 1 is uniform.

The embodiment of the application also discloses a connecting device for the guider blade, as shown in fig. 1 and 4, the connecting device is used for connecting the connecting pipe 3 to the guider blade 1, an inserting groove 19 for inserting the connecting pipe 3 is formed in the guider blade 1, and a fixing groove 17 is formed in the inner wall of the inserting groove 19.

As shown in fig. 5 and 6, the connecting device includes two half clamp rings 4, two first guide blocks 42 and a driving mechanism 5, the two half clamp rings 4 are slidably connected to the inner side wall of the fixing groove 17, the two half clamp rings 4 can form a complete ring after being spliced with each other, and the two half clamp rings 4 are used for fixing the connecting pipe 3 after being spliced with each other. All seted up spacing groove 41 in two half grip rings 4, fixedly connected with spacing ring 31 on the connecting pipe 3, spacing ring 31 is pegged graft with two spacing grooves 41 simultaneously and is cooperated.

Inclined planes are arranged on one sides, close to each other, of the two half clamping rings 4, the inclined planes of the two half clamping rings 4 are inclined downwards from one side, far away from the connecting pipe 3, to one side, near the connecting pipe 3, so that the limiting ring 31 can push the two half clamping rings 4 to move towards one side, far away from each other, and the connecting pipe 3 is convenient to be inserted into the insertion groove 19.

As shown in fig. 5 and 7, the two first guide blocks 42 are fixedly connected to the two half clamp rings 4 in a one-to-one correspondence manner, two first guide grooves 18 are formed in the fixing groove 17, and the two first guide blocks 42 are slidably connected to inner side walls of the two first guide grooves 18 in a one-to-one correspondence manner. The driving mechanism 5 is used for driving the two half clamping rings 4 to move towards one side close to the axial lead of the connecting pipe 3.

As shown in fig. 5, 6 and 7, the driving mechanism 5 includes two driving arc plates 51, two pushing gears 52, two second guide blocks 53 and a rotating assembly 54, wherein the two driving arc plates 51 are slidably connected to the inner wall of the fixing groove 17, and the opposite inner sides of the two driving arc plates 51 are in one-to-one corresponding contact with the opposite outer sides of the two half clamping rings 4. Wherein, one side of the driving arc plate 51 far away from the connecting pipe 3 is fixedly connected with a rack, one side of the driving arc plate 51 far away from the connecting pipe 3 is gradually reduced from one end to the other end of the driving arc plate away from the axial lead of the connecting pipe 3.

The two pushing gears 52 are rotatably connected to the inner side walls of the fixing grooves 17, and the two pushing gears 52 are meshed with the racks of the two driving arc-shaped plates 51 in a one-to-one correspondence manner. Two second guide blocks 53 correspond one-to-one and are fixedly connected to two driving arc-shaped plates 51, two second guide grooves for sliding the two second guide blocks 53 are formed in the fixing groove 17, and in order to reduce the friction force between the second guide blocks 53 and the second guide grooves, rollers or idler wheels can be installed on the second guide blocks 53.

As shown in fig. 5, 6 and 7, the rotating assembly 54 includes a driving gear 541 and a gear ring 542, the driving gear 541 and the gear ring 542 are rotatably connected to the inner sidewall of the fixing groove 17, gear teeth are fixedly connected to the inner circumferential surface and the outer circumferential surface of the gear ring 542, the gear teeth on the inner circumferential surface of the gear ring 542 are simultaneously engaged with the two pushing gears 52, and the gear teeth on the outer circumferential surface of the gear ring 542 are engaged with the driving gear 541.

The guide vane 1 is further 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 side wall of the fixing groove 17, and the screw 61 is fixedly connected with the driving gear 541. A sliding hole 171 is opened on an inner side wall of the fixing groove 17, and a portion of the pressing sleeve 62 is protruded out of the guide vane 1 through the sliding hole 171. The pressing sleeve 62 is slidably connected to the inner sidewall of the sliding hole 171, the pressing sleeve 62 is sleeved on the screw 61, and the pressing sleeve 62 is threadedly connected to the screw 61.

As shown in fig. 5 and 6, in the process of mounting the vane 1 on the turbine gate of the aircraft engine in a cold mounting manner, as the temperature on the vane 1 rises, the pressing sleeve 62 can gradually abut against the turbine gate and pushes the pressing sleeve 62 to move, the pressing sleeve 62 moves to push the screw 61 to rotate, the screw 61 rotates to drive the driving gear 541 to rotate, the driving gear 541 rotates to drive the driving gear 541 to rotate, the gear ring 542 rotates to drive the two pushing gears 52 to rotate, and the two pushing gears 52 rotate to drive the two driving arc plates 51 to move.

In the process of moving the two driving arc-shaped plates 51, the two half clamping rings 4 can be pushed to move under the shape action of the two driving arc-shaped plates 51, so that the two half clamping rings 4 move towards one side close to each other; after the limiting grooves 41 of the two half clamping rings 4 are matched with the limiting rings 31 on the connecting pipe 3, the two half clamping rings 4 are clamped between the connecting pipes 3, and the purpose of fixing the connecting pipes 3 is achieved.

The above are preferred embodiments of the present application, and the scope of protection of the present application is not limited thereto, so: all equivalent changes made according to the structure, shape and principle of the present application shall be covered by the protection scope of the present application.

Claims

1. A method for cooling a blade of a turbine guider of an aeroengine is characterized in that the method is applied to the blade (1) of the guider of the aeroengine, the blade (1) of the guider is provided with a cooling cavity (2), and the method comprises the following steps;

installing a cooling pipeline, a heat exchanger and an electromagnetic pump on an aircraft engine turbine gate, and adding cooling liquid into the cooling pipeline, wherein the heat exchanger and the electromagnetic pump are connected in series in the cooling pipeline, and a cooling cavity (2) in the guider blade (1) is communicated with the cooling pipeline through more than two connecting pipes (3) arranged on the cooling pipeline;

the electromagnetic pump is started, so that the cooling liquid flows into the cooling cavity (2) of the guide vane (1) from the cooling pipeline through the connecting pipe (3), and then the cooling liquid returns to the cooling pipeline from the cooling cavity (2) in the guide vane (1) through the other connecting pipe (3).

2. A method for cooling an aeroengine turbine vane (1) according to claim 1, wherein: the thickness of the front edge of the guide vane (1) is larger than that of the tail edge, the cooling cavity (2) of the guide vane (1) comprises a front edge cavity (21), a rear edge cavity (22) and a bottom cavity (23), the front edge cavity (21) is communicated with the bottom cavity (23) through a first cooling channel (11), and the bottom cavity (23) is communicated with the rear edge cavity (22) through a second cooling channel (12);

the way in which the cooling liquid flows through the cooling cavity (2) in the guide vane (1) comprises:

the cooling liquid sequentially passes through the front edge cavity (21), the first cooling channel (11), the bottom cavity (23), the second cooling channel (12) and the rear edge cavity (22) through the connecting pipe (3) and then returns to the cooling pipeline through the connecting pipe (3);

or;

the cooling liquid sequentially passes through the rear edge cavity (22), the second cooling channel (12), the bottom cavity (23), the first cooling channel (11) and the front edge cavity (21) through the connecting pipe (3) and then returns to the cooling pipeline through the connecting pipe (3).

3. The aircraft engine turbine guider blade (1) cooling method according to claim 1, wherein the thickness of the leading edge of the guider blade (1) is larger than that of the trailing edge, the cooling cavity (2) of the guider blade (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) is communicated with the leading edge bottom cavity (25) through a third cooling channel (13), the leading edge bottom cavity (25) is communicated with the transition cavity (24) through a fourth cooling channel (14), the transition cavity (24) is communicated with the trailing edge bottom cavity (26) through a fifth cooling channel (15), and the trailing edge bottom cavity (26) is communicated with the trailing edge cavity (22) through a sixth cooling channel (16);

the cooling liquid sequentially passes through a front edge cavity (21), a third cooling channel (13), a front edge bottom cavity (25), a fourth cooling channel (14), a transition cavity (24), a fifth cooling channel (15), a rear edge bottom cavity (26), a sixth cooling channel (16) and a rear edge cavity (22) through a connecting pipe (3) and then returns to the cooling pipeline through the connecting pipe (3);

or;

the cooling liquid sequentially passes through the rear edge cavity (22), the sixth cooling channel (16), the rear edge bottom cavity (26), the fifth cooling channel (15), the transition cavity (24), the fourth cooling channel (14), the front edge bottom cavity (25), the third cooling channel (13) and the front edge cavity (21) through the connecting pipe (3) and then returns to the cooling pipeline.

4. The aircraft engine turbine guider blade (1) cooling method according to claim 1, wherein the thickness of the leading edge of the guider blade (1) is larger than that of the trailing edge, the cooling cavity (2) of the guider blade (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) is communicated with the leading edge bottom cavity (25) through a third cooling channel (13), the leading edge bottom cavity (25) is communicated with the transition cavity (24) through a fourth cooling channel (14), the transition cavity (24) is communicated with the trailing edge bottom cavity (26) through a fifth cooling channel (15), and the trailing edge bottom cavity (26) is communicated with the trailing edge cavity (22) through a sixth cooling channel (16);

the cooling liquid respectively enters a front edge cavity (21) and a rear edge cavity (22) through two connecting pipes (3), and the cooling liquid entering the front edge cavity (21) sequentially passes through a third cooling channel (13), a front edge bottom cavity (25), a fourth cooling channel (14) and a transition cavity (24) and then returns to a cooling pipeline through the connecting pipes (3); and the cooling liquid entering the rear edge cavity (22) sequentially passes through the sixth cooling channel (16), the rear edge bottom cavity (26), the fifth cooling channel (15) and the transition cavity (24) and then returns to the cooling pipeline through the connecting pipe (3).

5. A connecting device for a vane, a method for cooling a vane of a turbine vane of an aircraft engine according to claim 1, wherein: the connecting device comprises a half clamping ring (4), a first guide block (42) and a driving mechanism (5);

an inserting groove (19) for inserting the connecting pipe (3) is formed in the guider blade (1), a fixing groove (17) is formed in the inner side wall of the inserting groove (19), and the half clamping ring (4) is connected with the fixing groove (17) in a sliding mode;

the half 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) is matched with 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 formed in the inner side wall of the fixing groove (17);

the driving mechanism (5) is used for driving the half clamping ring (4) to move.

6. A connecting device for a director blade (1) according to claim 5, characterised in that: an inclined plane is formed on the half clamping ring (4), and the inclined plane on the half clamping ring (4) is arranged downwards in an inclined mode from the side far away from the connecting pipe (3) to the side close to the connecting pipe (3).

7. A connecting device for a guide vane (1) according to claim 5, characterised in that: the driving mechanism (5) comprises a driving arc-shaped plate (51), a pushing gear (52) and a second guide block (53);

the driving arc-shaped plate (51) is connected with the inner side wall of the fixing groove (17) in a sliding mode, the driving arc-shaped plate (51) is far away from one side of the connecting pipe (3), the distance from one end of the driving arc-shaped plate (51) to the other end of the driving arc-shaped plate to the axial lead of the connecting pipe (3) is gradually reduced, and a rack is fixedly connected to one side, far away from the connecting pipe (3), of the driving arc-shaped plate (51);

the pushing gear (52) is rotatably connected with the inner side wall of the fixing groove (17), and the pushing gear (52) is meshed with the rack on the driving arc-shaped plate (51);

the second guide block (53) is fixedly connected to the driving arc-shaped plate (51), and a second guide groove for the second guide block (53) to slide is formed in the inner side wall of the fixing groove (17);

the driving mechanism (5) further comprises a rotating assembly (54) for driving the pushing gear (52) to rotate.

8. The connecting device for a director blade (1) according to claim 7, 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 rotatably installed on the inner side wall of the fixing groove (17);

gear teeth are fixedly connected to the outer circumferential surface and the inner circumferential surface of the gear ring (542), and the driving gear (541) is meshed with the gear teeth on the outer circumferential surface of the gear ring (542); the pushing gear (52) is meshed with gear teeth on the inner circumferential surface of the gear ring (542); and a driving assembly (6) for driving the driving gear (541) to rotate is further arranged on the inner side wall of the fixing groove (17).

9. The connecting device for a stator blade (1) according to claim 8, characterized in that: a sliding hole (171) is formed in the fixing groove (17), the driving assembly (6) comprises a screw rod (61) and a pressing sleeve (62), and the screw rod (61) is rotatably connected with the inner side wall of the fixing groove (17);

the screw rod (61) is fixedly connected with the driving gear (541), the pressing sleeve (62) is sleeved on the screw rod (61), and the screw rod (61) is in threaded connection with the pressing sleeve (62); the pressing sleeve (62) is connected with the side wall of the sliding hole (171) in a sliding mode, and one end of the pressing sleeve (62) protrudes out of the guide vane (1).