CN114838008B - Variable-angle reverse rotation nozzle vortex reduction system for radial inner flow disc cavity of gas compressor - Google Patents

Abstract

The invention discloses a vortex reducing system of a variable-angle reverse rotation nozzle of a radial inner flow disk cavity of a gas compressor, which comprises an axial gas-guiding section, a front stage gas compressor disk, a rear stage gas compressor disk and a drum barrel; two ends of the drum barrel are fixedly connected to the opposite inner sides of the front stage compressor disk and the rear stage compressor disk respectively, the front stage compressor disk, the rear stage compressor disk and the drum barrel enclose a disk cavity, and the disk cavity is communicated with the axial air entraining section; the side wall of the drum barrel is provided with a plurality of drum barrel holes along the circumferential direction of the drum barrel, and each drum barrel hole is communicated with the disc cavity; be provided with the nozzle baffle between preceding level compressor dish and the back level compressor dish, the lateral wall of nozzle baffle has set gradually a plurality of drainage holes along its circumference, be provided with variable angle derotation nozzle on the drainage hole. The invention can reduce the possibility of sudden drop of the bleed air flow and can adjust the bleed air flow according to the cold air flow required by the hot end part.

Description

A vortex reduction system for variable-angle reverse-swirl nozzles in the radial inner disk cavity of a compressor

technical field

The invention relates to the technical field of aero-engines, in particular to a vortex reduction system for a variable-angle reverse-swirl nozzle in a radial inner disk cavity of a compressor.

Background technique

At present, with the continuous development of the modern aviation industry, aero-engines are developing in the direction of 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, and increasing the compressor compression ratio can reduce fuel consumption. . Due to the limitation of the turbine material, the temperature of the turbine front blade must be cooled to a lower range. At present, the existing aero-engine cools the hot-end parts through the air system. The internal bleed air enters from the compressor drum hole, flows into the axial channel through the high-speed rotating compressor disc cavity, and finally enters the turbine disc. cavity. This radial air-entraining section is under a high centrifugal force field, and due to the development of free vortex, the existence of Coriolis force also hinders the radial inflow of gas. After the cooling gas is drawn from the appropriate part of the compressor, it passes through a designed flow channel and finally reaches the target position. In this bleed air channel, a series of pressure losses will occur, and the temperature of the cold air will increase accordingly. Therefore, a series of measures need to be taken in the design to reduce the pressure loss of the cold air as much as possible.

Existing aero-engines generally include an engine shaft and fans, compressors and turbines arranged in sequence along the axial direction of the engine shaft.

The most widely used vortex reducers at this stage are tubular vortex reducers, reverse swirl nozzle vortex reducers and finned vortex reducers. The installation of a vortex reducer between the bleed pan cavity can effectively limit the development of free vortex, thereby reducing the Coriolis force and centrifugal force, and reducing the pressure loss of gas.

However, these types of vortex reducers all have deficiencies. Among them, at a fixed angle, the anti-rotation nozzle is prone to an "S"-shaped change curve between the flow rate and the rotational speed, resulting in a mismatch between the flow rate and the rotational speed, and the problem of a sudden drop in the bleed air flow rate. .

Contents of the invention

The present application provides a vortex reduction system for a variable-angle reverse-swirl nozzle in a radially inner disk cavity of a compressor, which can reduce the possibility of a sudden drop in bleed air flow.

The application provides a vortex reduction system for a variable-angle reverse-swirl nozzle in the radial inner flow plate cavity of a compressor, which adopts the following technical scheme:

A vortex reduction system for variable-angle anti-rotation nozzles in the radial inner disk cavity of a compressor, including an axial air induction section, a front-stage compressor disk, a rear-stage compressor disk, and a drum; the two ends of the drum are respectively It is fixedly connected to the relative inner sides of the front-stage compressor disk and the rear-stage compressor disk. The front-stage compressor disk, the rear-stage compressor disk and the drum form a disk cavity, and the disk cavity communicates with the axial bleed section ; The side wall of the drum is provided with several drum holes along its circumference, and each of the drum holes is connected with the disk cavity; nozzles are arranged between the front stage compressor disk and the back stage compressor disk A partition, the side wall of the nozzle partition is sequentially provided with a plurality of drainage holes along its circumference, and the drainage holes are provided with variable-angle reverse-rotating nozzles.

By adopting the above technical scheme, when the compressor is running, several variable-angle reverse-rotating nozzles rotate coaxially, at the same speed, and in the same direction as the front-stage compressor disk and the rear-stage compressor disk, and the airflow flows through several The drum hole enters the disk cavity, and then the air is drawn into the axial air induction section by several variable-angle anti-rotation nozzles, and then the axial air induction section will introduce air into the turbine wheel rim; Under the action of the swirl nozzle, the possibility of a sudden drop in the bleed air flow rate can be reduced and it can be adjusted according to the cold air flow rate required by the hot end components.

Preferably, the variable-angle anti-rotation nozzle includes a fixed section and a variable section, the fixed section is affixed to the side wall of the drainage hole, and the variable section is movably connected to the fixed section; the vortex reduction system also includes The drive assembly used to drive the variable segment to rotate.

By adopting the above technical solution, when the compressor is at different speeds and the air flow into the disk cavity through the drum hole is different, by adjusting the angle of the variable section, the air flow loss can be reduced, thereby facilitating the adjustment of the turbine. The roulette is cooled. When the angle of the variable section needs to be adjusted, it can be realized through the driving assembly.

Preferably, a first spherical tube is provided at the end of the fixed section away from the nozzle baffle, a second spherical tube is provided at the end of the variable section close to the nozzle baffle, and the second spherical tube is rotatably connected to the first spherical tube. tube, and the first spherical tube is sealingly connected with the second spherical tube.

By adopting the above technical solution, the first spherical tube and the second spherical tube are provided to facilitate the rotation of the variable section in the fixed section, thereby facilitating the adjustment of the angle of the variable section; in addition, the first spherical tube and the second spherical tube The tubes are tightly connected, which reduces the possibility of air leakage from the junction of the first bulb and the second bulb.

Preferably, the drive assembly includes a plurality of first electric steering gears installed on the first spherical tubes in one-to-one correspondence, and the output shaft of the first electric steering gear runs through the side wall of the first spherical tube and the second The spherical tube is fixed.

By adopting the above technical scheme, when it is necessary to drive the variable segment to rotate, start the first electric steering gear, and at this time the output shaft of the first electric steering gear can drive the variable segment to rotate; , it is convenient to drive multiple variable segments to rotate in one-to-one correspondence.

Preferably, the drive assembly includes a second electric steering gear installed on the outer wall of a first spherical tube, the output shaft of the second electric steering gear passes through the side wall of the first spherical tube and is fixedly connected to the second spherical tube; The outer wall of each second spherical tube is fixed with a rotating shaft, and the rotating shaft is rotatably connected to the first spherical tube and the front-stage compressor disk; each end of the rotating shaft away from the first spherical tube runs through the front-stage compressor The disk is provided with and fixedly connected with gears, and a ring gear is rotatably connected to the disk of the front-stage compressor, and a plurality of the gears are all engaged with the ring gear.

By adopting the above-mentioned technical scheme, when the variable section needs to be driven to rotate, the output shaft of the second electric steering gear drives a second spherical tube to rotate, and the second spherical tube rotates to drive a rotating shaft to rotate, and the rotating shaft drives to be installed on it The gear rotates, the gear rotates to drive the ring gear to rotate, the ring gear rotates to drive the rest of the gears to rotate, and the rest of the gears can drive the rest of the variable segments to rotate. The production cost of the compressor can be reduced.

Preferably, the inlet plane of the variable-angle reverse-rotation nozzle and the tangent to the circle where the center point of the variable-angle reverse-rotation nozzle inlet forms an included angle α, and the included angle α is consistent with the flow direction of the airflow.

By adopting the above technical solution, the air flow loss can be reduced, thereby facilitating the cooling of the turbine disc.

Preferably, the outlet plane of the variable-angle reverse-rotation nozzle and the tangent to the circle where the center point of the variable-angle reverse-rotation nozzle outlet forms an included angle β, and the range of the included angle β that can be adjusted is 0°-90°.

By adopting the above technical solution, the outlet angle of the airflow can be adjusted, so that the flow capacity of the vortex reducing system can be adjusted, thereby achieving the effect of adjusting the flow rate of the bleed air.

Preferably, the outer radius of the front-stage compressor disk and the rear-stage compressor disk is Rb, the inner radius of the front-stage compressor disk and the rear-stage compressor disk is Ra, and the inlet of the variable-angle reverse rotation nozzle is The central radius is R1, and the central radius of the outlet of the variable-angle reverse-rotation nozzle is R2, wherein R1 is 0.5Rb-0.6Rb, and R2 is 0.45-0.55Rb.

By adopting the above technical solution, the position of the variable-angle reverse-rotation nozzle is too high or too low to increase the loss of airflow flow. According to the above-mentioned settings, the variable-angle reverse-rotation nozzle can be placed in a better position, thereby reducing the flow of airflow loss.

Preferably, each of the drum holes is an oblong hole.

By adopting the above technical solution, it is convenient to reduce the flow loss of the air flow.

In summary, the application has the following beneficial effects:

1. When the compressor is running, several variable-angle reverse-rotating nozzles rotate coaxially, at the same speed, and in the same direction as the front-stage compressor disk and the rear-stage compressor disk. At this time, the air flows through several drum holes and enters In the disc cavity, the air is drawn into the axial air induction section by several variable angle anti-rotation nozzles, and then the axial air induction section will introduce air into the turbine wheel rim; at this time, the role of the variable angle anti-rotation nozzles The possibility of a sudden drop in the bleed air flow rate can be reduced;

2. When the compressor is at different speeds and the air flow into the disc cavity through the drum hole is different, by adjusting the angle of the variable section, the loss of air flow can be reduced, thereby facilitating the cooling of the turbine disc . When it is necessary to adjust the angle of the variable section, it can be realized through the drive assembly;

3. When the variable section needs to be driven to rotate, the output shaft of the second electric steering gear drives a second spherical tube to rotate, the rotation of the second spherical tube drives a rotating shaft, and the rotating shaft drives the gear mounted on it to rotate, The rotation of the gear drives the rotation of the ring gear, the rotation of the ring gear drives the rotation of the other gears, and the rotation of the other gears can drive the rotation of the other variable segments; in summary, through the set drive assembly, it is convenient to drive multiple variable segments to rotate at the same time, so that the compressor can be reduced. production cost.

Description of drawings

Fig. 1 is the overall structure schematic diagram of embodiment one;

Fig. 2 is a schematic structural view highlighting the variable-angle reverse-rotating nozzle in Embodiment 1;

Fig. 3 is a partial sectional view highlighting the internal structure of the first spherical tube in Embodiment 1;

Fig. 4 is a partial sectional view of the protrusion driving assembly in the second embodiment.

Explanation of reference signs: 1. Axial bleed air section; 2. Front-stage compressor disk; 3. Back-stage compressor disk; 4. Drum; 41. Disk cavity; 42. Drum hole; 5. Nozzle partition ;51, drainage hole; 6, variable angle anti-rotation nozzle; 61, fixed section; 611, first spherical tube; 62, variable section; 621, second spherical tube; 63, metal sealing ring; 7, drive assembly ; 71, the first electric steering gear; 72, the second electric steering gear; 73, the rotating shaft; 74, the gear; 75, the ring gear.

Detailed ways

The present invention will be described in further detail below in conjunction with the accompanying drawings. Wherein the same components are denoted by the same reference numerals. It should be noted that the words "front", "rear", "left", "right", "upper", "lower", "bottom" and "top" used in the following description refer to the Directions, the words "inner" and "outer" refer to directions toward or away from, respectively, the geometric center of a particular component.

Embodiment one

The invention discloses a vortex reduction system for variable-angle anti-rotation nozzles in the radial inner flow plate cavity of a compressor, as shown in Figures 1 and 2, comprising an axial air induction section 1, a front-stage compressor disk 2, and a rear-stage compressor Disk 3 and drum 4; axial air-introduction section 1, compressor disk 2 of the front stage and compressor disk 3 of the rear stage are coaxial, and the two ends of the drum 4 are fixedly connected to the compressor disk 2 of the front stage and the rear The relative inner side of the stage compressor disk 3, the front stage compressor disk 2, the rear stage compressor disk 3 and the drum 4 form a disk cavity 41, and the disk cavity 41 communicates with the axial air-inducing section 1; the side wall of the drum 4 A number of drum holes 42 are sequentially arranged along its circumference, and each drum hole 42 is an oblong hole, and each drum hole 42 communicates with the disc cavity 41 . In the related art, multiple front-stage compressor disks 2 and rear-stage compressor disks 3 are arranged alternately, and drums 4 are arranged between adjacent front-stage compressor disks 2 and rear-stage compressor disks 3 .

As shown in Figure 1 and Figure 2, a nozzle partition 5 is arranged between the front stage compressor disk 2 and the rear stage compressor disk 3, and the two ends of the nozzle partition 5 are fixedly connected to the front stage compressor disk 2 and the rear stage respectively. On the relative inner side of the stage compressor disk 3, the nozzle partition 5 is in the shape of a ring, and the side wall of the nozzle partition 5 is provided with a plurality of drainage holes 51 in sequence along its circumference, and the drainage holes 51 are provided with variable-angle reverse-rotation nozzles. 6. When the compressor is running, several variable-angle reverse-rotating nozzles 6 rotate coaxially, at the same speed, and in the same direction as the front-stage compressor disk 2 and the rear-stage compressor disk 3, and the airflow flows through several drum holes at this time 42 enters the disk cavity 41, and then is drawn into the axial air-introduction section 1 by several variable-angle anti-rotation nozzles 6, and then the axial air-induction section 1 will introduce air into the turbine wheel rim; Under the action of the angle counter-rotating nozzle 6, the possibility of a sudden drop in the bleed air flow rate can be reduced.

As shown in Figures 2 and 3, the variable-angle reverse-rotation nozzle 6 includes a fixed section 61 and a variable section 62, the fixed section 61 is fixed to the side wall of the drainage hole 51, and the variable section 62 is movably connected to the fixed section 61, The shapes of the fixed section 61 and the variable section 62 can be cylindrical but not limited to cylindrical; the vortex reduction system also includes a driving assembly 7 for driving the variable section 62 to rotate. When the compressor is at different rotational speeds and the air flow into the disc cavity 41 through the drum hole 42 is different, by adjusting the angle of the variable section 62, the loss of the air flow can be reduced, thereby facilitating the adjustment of the turbine disc. cool down. When the angle of the variable section 62 needs to be adjusted, it can be realized through the driving assembly 7 .

As shown in Figures 2 and 3, the end of the fixed section 61 away from the nozzle baffle 5 is provided with a first spherical tube 611, and the end of the variable section 62 close to the nozzle baffle 5 is provided with a second spherical tube 621, the second spherical tube 621 is embedded and rotationally connected to the first spherical tube 611 , and the first spherical tube 611 and the second spherical tube 621 are sealed and connected by a metal sealing ring 63 . The first spherical tube 611 and the second spherical tube 621 facilitate the rotation of the variable section 62 in the fixed section 61, thereby facilitating the adjustment of the angle of the variable section 62; in addition, the first spherical tube 611 and the second spherical tube The tubes 621 are tightly connected, which can reduce the possibility of air leakage from the joints of the first spherical tube 611 and the second spherical tube 621 .

As shown in FIGS. 2 and 3 , the driving assembly 7 includes a plurality of first electric steering gears 71 mounted on the outer walls of a plurality of first spherical tubes 611 in one-to-one correspondence, and the output shafts of the first electric steering gears 71 pass through the first The side wall of the spherical tube 611 is fixedly connected to the second spherical tube 621 ; the connection between the output shaft of the first electric steering gear 71 and the first spherical tube 611 is connected through a rotary seal. When it is necessary to drive the variable section 62 to rotate, start the first electric steering gear 71, and now the output shaft of the first electric steering gear 71 can drive the variable section 62 to rotate; It is convenient to drive a plurality of variable segments 62 to rotate in one-to-one correspondence.

As shown in Figure 2, the inlet plane of the variable-angle reverse-rotation nozzle 6 and the tangent line of the circumference of the variable-angle reverse-rotation nozzle 6 inlet center point form an included angle α, and the included angle α is consistent with the flow direction of the airflow, which can reduce the flow loss of the airflow , so as to facilitate the cooling of the turbine disc. The outlet plane of the variable-angle reverse-rotation nozzle 6 and the tangent line of the circle where the outlet center point of the variable-angle reverse-rotation nozzle 6 is located form an angle β, and the range of the angle β that can be adjusted is 0°-90°; in this way, the air outlet angle can be adjusted, Therefore, the flow capability of the vortex reduction system can be adjusted, and thus the effect of adjusting the bleed air flow can be achieved.

As shown in Figure 2, the outer radius of the front-stage compressor disk 2 and the rear-stage compressor disk 3 is Rb, the inner radius of the front-stage compressor disk 2 and the rear-stage compressor disk 3 is Ra, and the variable-angle reverse-rotation nozzle 6 The central radius of the inlet is R1, and the central radius of the outlet of the variable-angle reverse-rotating nozzle 6 is R2, wherein R1 is 0.5Rb-0.6Rb, and R2 is 0.45-0.55Rb. Because the position of the variable-angle reverse-rotation nozzle 6 is too high or too low, the airflow loss will be increased. According to the above setting, the variable-angle reverse-rotation nozzle 6 can be in a better position, thereby reducing the airflow loss.

Working principle: When the compressor is running, several variable-angle reverse-rotating nozzles 6 rotate coaxially, at the same speed, and in the same direction as the front-stage compressor disk 2 and the rear-stage compressor disk 3. At this time, the airflow flows through several drums The barrel hole 42 enters the disc cavity 41, and then the air is led into the axial air-introduction section 1 by several variable-angle reverse-rotation nozzles 6, and then the axial air-induction section 1 will introduce air into the turbine wheel rim; Under the action of the variable-angle reverse-rotating nozzle 6, the possibility of a sudden drop in the bleed air flow rate can be reduced.

Embodiment two

As shown in Figure 4, the main difference from Embodiment 1 is that the driving assembly 7 includes a second electric steering gear 72 installed on the outer wall of a first spherical tube 611, and the output shaft of the second electric steering gear 72 runs through the first spherical tube. The side wall of the tube 611 is fixedly connected to the second spherical tube 621, and the connection between the output shaft of the second electric steering gear 72 and the first spherical tube 611 is connected through a rotary seal; the outer wall of each second spherical tube 621 is fixedly connected There is a rotating shaft 73, and the rotating shaft 73 is arranged along the axial direction of the nozzle partition plate 5. The rotating shaft 73 is rotatably connected to the first spherical tube 611 and the front-stage compressor disk 2 through a rotary seal; each rotating shaft 73 is penetrated by one end away from the first spherical tube 611 The front-stage compressor disc 2 is provided with and fixedly connected with a gear 74, and the front-stage compressor disc 2 is rotatably connected with a ring gear 75. engage. When it is necessary to drive the variable section 62 to rotate, the output shaft of the second electric steering gear 72 drives a second spherical tube 621 to rotate, and the rotation of the second spherical tube 621 drives a rotating shaft 73 to rotate, and the rotating shaft 73 drives to be installed on it The gear 74 rotates, the gear 74 rotates to drive the ring gear 75 to rotate, the ring gear 75 rotates to drive the remaining gears 74 to rotate, and the rotation of the remaining gears 74 can drive the remaining variable segments 62 to rotate; A plurality of variable segments 62 rotate, so that the production cost of the compressor can be reduced.

All of the above are preferred embodiments of the present application, and are not intended to limit the protection scope of the application. Therefore, all equivalent changes made according to the structure, shape and principle of the application should be covered by the protection scope of the application. Inside.

Claims (5)

1. A variable-angle derotation nozzle vortex reduction system of a radial inner flow disk cavity of a gas compressor is characterized by comprising: the device comprises an axial air-entraining section (1), a front stage compressor disk (2), a rear stage compressor disk (3) and a drum barrel (4); two ends of the drum (4) are fixedly connected to the opposite inner sides of the front-stage compressor disk (2) and the rear-stage compressor disk (3) respectively, the front-stage compressor disk (2), the rear-stage compressor disk (3) and the drum (4) enclose a disk cavity (41), and the disk cavity (41) is communicated with the axial air-entraining section (1);

the side wall of the drum barrel (4) is provided with a plurality of drum barrel holes (42) along the circumferential direction, and each drum barrel hole (42) is communicated with the disc cavity (41);

a nozzle partition plate (5) is arranged between the front stage compressor disk (2) and the rear stage compressor disk (3), a plurality of drainage holes (51) are sequentially formed in the side wall of the nozzle partition plate (5) along the circumferential direction of the nozzle partition plate, and variable-angle counter-rotating nozzles (6) are arranged on the drainage holes (51);

the variable-angle counter-rotating nozzle (6) comprises a fixed section (61) and a variable section (62), the fixed section (61) is fixedly connected to the side wall of the drainage hole (51), and the variable section (62) is movably connected to the fixed section (61); the vortex reduction system further comprises a drive assembly (7) for driving the variable section (62) to rotate;

a first spherical pipe (611) is arranged at one end, away from the nozzle partition plate (5), of the fixed section (61), a second spherical pipe (621) is arranged at one end, close to the nozzle partition plate (5), of the variable section (62), the second spherical pipe (621) is rotatably connected to the first spherical pipe (611), and the first spherical pipe (611) is in sealing connection with the second spherical pipe (621);

the driving assembly (7) comprises a second electric steering engine (72) arranged on the outer side wall of the first spherical pipe (611), and an output shaft of the second electric steering engine (72) penetrates through the side wall of the first spherical pipe (611) and is fixedly connected with the second spherical pipe (621); the outer side wall of each second spherical pipe (621) is fixedly connected with a rotating shaft (73), and the rotating shaft (73) is rotatably connected with the first spherical pipe (611) and the front stage compressor disc (2); one end, far away from the first spherical pipe (611), of each rotating shaft (73) penetrates through the front stage compressor disk (2) and is fixedly connected with a gear (74), the front stage compressor disk (2) is rotatably connected with a gear ring (75), and the gears (74) are meshed with the gear ring (75);

when the variable section (62) is driven to rotate, an output shaft of the second electric steering engine (72) drives a second spherical pipe (621) to rotate, the second spherical pipe (621) rotates to drive a rotating shaft (73) to rotate, the rotating shaft (73) rotates to drive a gear (74) arranged on the rotating shaft to rotate, the gear (74) rotates to drive a gear ring (75) to rotate, the gear ring (75) rotates to drive other gears (74) to rotate, and the other gears (74) rotate to drive other variable sections (62) to rotate.

2. The de-swirl nozzle vortex reduction system of claim 1, wherein: the inlet plane of the variable-angle reverse rotation nozzle (6) and the circumferential tangent line where the central point of the inlet of the variable-angle reverse rotation nozzle (6) is located form an included angle alpha, and the included angle alpha is consistent with the flowing direction of the airflow.

3. The de-swirl nozzle vortex reduction system of claim 1, wherein: the outlet plane of the variable-angle reverse rotation nozzle (6) and the circumferential tangent line where the central point of the outlet of the variable-angle reverse rotation nozzle (6) is located form an included angle beta, and the adjustable range of the included angle beta is 0-90 degrees.

4. The de-swirl nozzle vortex reduction system of claim 1, wherein: the outer radius of the front stage compressor disk (2) and the outer radius of the rear stage compressor disk (3) are Rb, the inner radius of the front stage compressor disk (2) and the inner radius of the rear stage compressor disk (3) are Ra, the inlet center radius of the variable-angle reverse rotation nozzle (6) is R1, the outlet center radius of the variable-angle reverse rotation nozzle (6) is R2, wherein R1 is 0.5Rb-0.6Rb, and R2 is 0.45-0.55Rb.

5. The de-swirl nozzle vortex reduction system of claim 1, wherein: each drum hole (42) is an oblong hole.

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