CN115853598B - Turbine blade cold air supercharging impeller for axial air intake and pre-rotation supercharging air supply system - Google Patents
Turbine blade cold air supercharging impeller for axial air intake and pre-rotation supercharging air supply system Download PDFInfo
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- CN115853598B CN115853598B CN202211512040.5A CN202211512040A CN115853598B CN 115853598 B CN115853598 B CN 115853598B CN 202211512040 A CN202211512040 A CN 202211512040A CN 115853598 B CN115853598 B CN 115853598B
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Abstract
The invention discloses a turbine blade cold air supercharging impeller for axial air intake and a pre-rotation supercharging air supply system, wherein the turbine blade cold air supercharging impeller comprises a supercharging impeller body and impeller blades, the supercharging impeller body is annular, and a runner is arranged in the supercharging impeller body; one side of the booster impeller body is provided with an air inlet, and the other side of the booster impeller body is provided with an air outlet; the air inlet and the air outlet are communicated with the flow channel; the impeller blades are arranged at the air inlet and used for driving air to enter the flow channel when the booster impeller body rotates. The invention can efficiently perform cold air supercharging on the low-pressure turbine rotor of the high-radius air inlet pre-rotation nozzle.
Description
Technical Field
The invention relates to the technical field of supercharging impellers, in particular to an axial air inlet turbine blade cold air supercharging impeller and a pre-rotation supercharging air supply system.
Background
The cold air booster impeller is an important structure in the turbine structure. In the prior art, various related structures are disclosed, such as a turbine bucket cooling air segmented rotary booster wheel disclosed in the document of patent No. 202011163888.2, a turbine rotor with a cooled bleed air booster wheel disclosed in the document of patent No. 202010760082.5, a turbine bucket cooling air booster wheel disclosed in the document of patent No. 202011164899.2, a rotary booster structure for turbine bucket cooling disclosed in the document of patent No. 202010756476.3, and the like.
In the structure disclosed in the above patent documents, all designs are made for the low-radius position air inlet pre-rotation nozzle, and when the designs are matched with the high-radius position air inlet pre-rotation nozzle, some designs cannot realize cold air increase, such as 202010760082.5 and 202010756476.3; when some of the air inlet pre-rotation nozzles are matched with the air inlet pre-rotation nozzles at the high radius positions, air flow needs to impact on the supercharging impeller firstly, then flows inwards in the radial direction, finally turns 180 degrees and then flows outwards in the radial direction, so that larger flow loss is caused, and the supercharging effect is poor, for example, patent documents 202011163888.2 and 202011164899.2.
The main reason for the problems is that the documents are mostly applied to cold air supercharging of high-pressure turbine rotor blades of aeroengines and gas turbines, and low-radius air inlet pre-spinning nozzles are mostly adopted. For the cool air supercharging of the low-pressure turbine rotor impeller blades, the air inlet pre-spinning nozzle adopts a high-radius air inlet pre-spinning nozzle, and the low-pressure turbine with the air inlet pre-spinning nozzle arranged at the high-radius position cannot be adapted to the various structures.
In view of the foregoing, how to efficiently cool air boost a low pressure turbine rotor provided with a high-radius intake pre-rotation nozzle is one of the important problems to be solved in the art.
Disclosure of Invention
The invention aims to provide an axial air inlet turbine blade cold air supercharging impeller and a pre-rotation supercharging air supply system, which are used for solving the defects in the prior art and can be used for efficiently carrying out cold air supercharging on a low-pressure turbine rotor of a high-radius air inlet pre-rotation nozzle.
The invention provides a turbine blade cold air supercharging impeller for axial air intake, which comprises,
the supercharging impeller body is annular, and a runner is arranged in the supercharging impeller body; one side of the booster impeller body is provided with an air inlet, and the other side of the booster impeller body is provided with an air outlet; the air inlet and the air outlet are communicated with the flow channel; the air inlet direction of the air inlet is parallel to the axis of the booster impeller body;
the impeller blades are arranged in the flow channel, and the blades are used for driving air to enter from the air inlet and flow outwards in the radial direction when the impeller body rotates.
The turbine blade cold air supercharging impeller for axial air intake, wherein optionally, the air inlet is annular, and the number of the impeller blades is a plurality of impeller blades;
the impeller blades are distributed in a circumferential array along the direction of the air inlet.
The axially-fed turbine-blade cold air booster impeller as described above, wherein, optionally, the impeller blades are inclined in a radially outward direction, either both clockwise or both counter-clockwise.
The turbine blade cold air boost impeller of axial air intake as described above, wherein optionally the radius of rotation of the air outlet is greater than the radius of rotation of the air inlet.
The turbine blade cold air supercharging impeller with axial air inlet, wherein optionally, one side of the supercharging impeller body with the air inlet is provided with a comb ring;
the periphery of the comb tooth ring is provided with comb teeth;
the radius of the comb ring is larger than the rotation radius of the air inlet.
An axially-admitted turbine blade cold air boost impeller as described above, wherein optionally the impeller blades are twisted by the inlet and extend into the flow passage such that the direction of air flow compressed by the impeller blades is changed from axial to radial outwardly.
The invention also provides a cold air pre-rotation supercharging air supply system, which comprises a turbine disk, a pre-rotation nozzle, turbine blades and the turbine blade cold air supercharging impeller;
the turbine blades are mounted at the periphery of the turbine disc through tenons;
the turbine disc is provided with an air supply hole, one end of the air supply hole is positioned on the end face of the turbine disc, and the other end of the air supply hole is positioned at the root of a mortise of the turbine disc; the air supply hole is used for supplying air into the turbine blade;
the supercharging impeller body is fixedly arranged on the turbine disc, and an air outlet on the supercharging impeller body is communicated with the air supply hole.
The cold air pre-rotation booster air supply system as described above, wherein, optionally, the air supply hole is inclined outwardly in a direction away from the booster impeller body.
A chilled air pre-swirl pressurized air supply system as described above wherein, optionally, the air inlet is directly opposite the pre-swirl nozzle.
The cold air pre-rotation pressurizing air supply system, wherein optionally, the tenon is arranged on the turbine blade and is connected with the tenon groove of the turbine disc;
the air supply hole is communicated with the tenon.
Compared with the prior art, the integrated air inlet booster impeller body is arranged, the air inlet of the air inlet booster impeller body is directly arranged to be axially air-inlet, and the air inlet is opposite to the pre-rotation nozzle, so that the radial flowing distance of air is reduced, the direction of the air in the flowing process is changed, the flowing loss of the air can be greatly reduced, and the booster effect is improved.
Drawings
Fig. 1 is a perspective view of a booster impeller according to embodiment 1 of the present invention;
fig. 2 is a perspective view of the booster impeller according to embodiment 1 of the present invention from another perspective.
FIG. 3 is a schematic cross-sectional view of a booster impeller according to embodiment 1 of the present invention;
fig. 4 is a schematic view showing a mounting structure of a booster impeller according to embodiment 2 of the present invention.
Reference numerals illustrate:
1-a booster impeller body, 2-a turbine disc, 3-turbine blades and 4-a honeycomb structure;
11-air inlets, 12-impeller blades, 13-comb tooth rings and 14-comb teeth;
21-air supply hole, 22-pre-rotation nozzle and 23-tenon.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In order to solve the problems indicated in the background art, the present invention proposes the following solution for improving the efficient cold air pressurization of the low pressure turbine rotor of the inlet pre-rotation nozzle with a high radius.
Example 1
Referring to fig. 1 to 3, the present embodiment provides an axial air intake turbine vane cold air supercharging impeller, wherein: comprising a booster impeller body 1 and impeller blades 12. The booster impeller body 1 is used for rotating together with turbine blades, and the air is compressed by the rotation of the booster impeller body 1 and the impeller blades 12.
The supercharging impeller body 1 is annular, and a flow passage is arranged in the supercharging impeller body 1; one side of the booster impeller body 1 is provided with an air inlet 11, and the other side is provided with an air outlet; the air inlet 11 and the air outlet are both communicated with the flow channel. In practice, the air inlet 11 is parallel to the center line of the booster impeller body 1, i.e. axial air intake can be achieved. Because the pre-rotation nozzle is axially air-out, the air inlet 11 is axially arranged and is opposite to the outlet of the pre-rotation nozzle, and the air flow resistance during supercharging of the supercharging impeller body 1 can be reduced.
The impeller blades 12 are arranged at the air inlet 11, the impeller blades 12 being adapted to drive air into the flow channel when the impeller body 1 is rotated. In particular, the air inlet 11 is annular. In specific implementation, the impeller blades 12 are integrally provided with the impeller body 1.
In specific implementation, the booster impeller body 1 is axially charged, and when gas flows into the flow channel of the booster impeller body 1 from the pre-rotation nozzle, the gas inlet 11 is opposite to the pre-rotation nozzle, so that the energy loss of gas flow can be reduced, and the booster efficiency is further improved. The supercharging impeller provided by the embodiment is particularly suitable for cold air supercharging of low-pressure turbine rotor impeller blades, and particularly suitable for low-pressure turbines provided with air inlet pre-spinning nozzles at high-radius positions.
Specifically, the air inlet 11 is annular, and the number of the impeller blades 12 is a plurality; a plurality of the impeller blades 12 are distributed in a circumferential array along the direction of the air inlet 11. In practice, flanges may be disposed on two sides of the air inlet 11, so as to implement axial arrangement of the air inlet 11.
To ensure a supercharging effect, the impeller blades 12 are inclined in the radial outward direction, either clockwise or counter-clockwise. The inclination direction of the impeller blades 12 is related to the design rotation direction of the booster impeller body 1, so long as the booster impeller body 1 can be ensured to compress the gas to the flow passage when rotating with the turbine. More specifically, the impeller blades 12 are twisted by the intake port 11 and extend into the flow passage so that the direction of the air flow compressed by the impeller blades 12 changes from the axial direction to the radial direction. That is, the impeller blades 12 are three-dimensionally curved impeller blade shapes rather than the constant cross-section straight impeller blade shapes of the prior art. By the modeling mode of the impeller blades, the axial air inlet of the axial air inlet booster impeller 13 is realized, and the air enters the flow passage along the radial direction. Meanwhile, the radius of rotation of the air outlet is larger than that of the air inlet 11. Thus, the direction change of the air flow can be reduced as much as possible, which is beneficial to reducing the air flow resistance.
In one implementation, the side of the impeller body 1 having the air inlet 11 is provided with a comb ring 13, and the comb ring 13 is used for matching with the honeycomb structure 4 on other components. The supercharging impeller body 1, the comb ring 13 and the fastening structure are integrally designed, so that the axial air inlet supercharging impeller can be used for supercharging cold air, the comb seal structure is formed by matching the axial air inlet supercharging impeller with the honeycomb structure 4, the axial air inlet supercharging impeller can be conveniently fastened on the turbine disc, the number of parts is reduced, and the structural rigidity is improved. More specifically, the periphery of the comb ring 13 is provided with comb teeth 14; the radius of the comb ring 13 is larger than the radius of rotation of the intake port 11. More specifically, the grate teeth 14 are annularly arranged along the outer periphery of the grate ring 13; the number of the comb teeth 14 is at least two.
Example 2
The embodiment is a specific application of embodiment 1, and the same points are not described again, and only the differences are described below.
Referring to fig. 4, the present embodiment provides a cool air pre-rotation supercharging air supply system, which includes a turbine disk 2, turbine blades 3 and a supercharging impeller as disclosed in embodiment 1.
Specifically, the turbine blade 3 is mounted on the outer periphery of the turbine disk 2. The turbine disc 2 drives the turbine blades 3 to rotate. More specifically, the turbine disc 2 is provided with an air supply hole 21, one end of which is located at the end face of the turbine disc 2, and the other end of which is located at the outer circumferential face of the turbine disc 2; the air supply hole 21 is used for supplying air into the turbine blade 3. The booster impeller body 1 is fixedly arranged on the turbine disc 2, and an air outlet on the booster impeller body 1 is communicated with the air supply hole 21. The air supply hole 21 communicates with the tenon 23. In particular, the air inlet 11 is opposite to the pre-rotation nozzle 22. Still further, a tenon 23 is further included, and the tenon 23 is disposed on the turbine blade 3 and fixedly connected to the turbine disc 2.
When the gas flow system is specifically used, the flow mode of the gas is as follows: the cool air is discharged from the pre-rotation nozzle 22, enters the air inlet 11 along the axial direction, flows through the flow passage, flows from the air supply hole 21 to the root of the dovetail groove of the mounting dovetail 23, and then flows into the turbine blade 2 through the radial direction Kong Zailiu inside the dovetail 23, thereby finally cooling the turbine blade 2.
In practice, the turbine disk 2 is radially from the inside to the outside, respectively a hub, a web and a rim. The left side of the disk hub extends out of the extending arm with the honeycomb structure and is matched with an external comb ring to form a comb seal structure. The turbine blade 3 is mounted in a dovetail groove in the rim of the turbine disk 2 by means of a dovetail 23.
In practice, the air supply holes 21 are inclined outwardly in a direction away from the booster impeller body 1. This arrangement can advantageously reduce the resistance of the air flow when passing through the air supply holes 21.
With the above structure, the arrangement of the supercharging impeller when the pre-rotation nozzle 22 is in the higher radius position and the effect of the efficient, low-loss supercharging of the cooling air can be achieved. Specifically, the integrated air inlet booster impeller body is arranged, the air inlet of the air inlet booster impeller body is directly arranged to be axially air-inlet, and the air inlet is opposite to the pre-rotation nozzle, so that the radial flowing distance of the air is reduced, the direction of the air in the flowing process is changed, the flowing loss of the air can be greatly reduced, and the booster effect is improved.
While the foregoing is directed to embodiments of the present invention, other and further embodiments of the invention may be devised without departing from the basic scope thereof, and the scope thereof is determined by the claims that follow.
Claims (3)
1. The cold air pre-rotation supercharging air supply system is characterized by comprising a turbine disc (2), a pre-rotation nozzle, turbine blades (3) and a turbine blade cold air supercharging impeller for axially feeding air;
the axially-admitted turbine blade cold air boost impeller comprises,
the supercharging impeller comprises a supercharging impeller body (1), wherein the supercharging impeller body (1) is annular, and a flow passage is arranged in the supercharging impeller body (1); one side of the booster impeller body (1) is provided with an air inlet (11), and the other side is provided with an air outlet; the air inlet (11) and the air outlet are communicated with the flow channel; the air inlet direction of the air inlet (11) is parallel to the axis of the booster impeller body (1);
impeller blades (12), wherein the impeller blades (12) are arranged in the flow channel, and the impeller blades (12) are used for driving air to enter from the air inlet (11) and flow outwards in the radial direction when the supercharging impeller body (1) rotates;
the impeller blades (12) are twisted by the air inlet (11) and extend into the flow channel so that the direction of air flow compressed by the impeller blades (12) is changed from axial direction to radial direction outwards;
the impeller blades (12) adopt three-dimensional bending impeller blade modeling, and the axial air inlet of the turbine blade cold air supercharging impeller is realized in a three-dimensional bending impeller blade modeling mode, so that air enters the flow passage along the radial direction; the radius of rotation of the air outlet is larger than that of the air inlet (11);
the air inlet (11) is annular, and the impeller blades (12) are multiple in number;
a plurality of impeller blades (12) are distributed in a circumferential array along the direction of the air inlet (11);
the impeller blades (12) are inclined in a clockwise direction or in a counter-clockwise direction in a radially outward direction;
one side of the supercharging impeller body (1) with the air inlet (11) is provided with a comb ring (13);
the periphery of the comb tooth ring (13) is provided with comb teeth (14);
the radius of the comb tooth ring (13) is larger than the rotation radius of the air inlet (11);
the turbine blades (3) are mounted at the periphery of the turbine disc (2) by tenons (23);
an air supply hole (21) is formed in the turbine disc (2), one end of the air supply hole is positioned on the end face of the turbine disc (2), and the other end of the air supply hole is positioned at the root of a tongue-and-groove of the turbine disc (2); the air supply hole (21) is used for supplying air into the turbine blade (3);
the supercharging impeller body (1) is fixedly arranged on the turbine disk (2), and the air outlet on the supercharging impeller body (1) is communicated with the air supply hole (21);
the air inlet (11) is opposite to the pre-rotation nozzle (22).
2. The cold air pre-rotation booster air supply system according to claim 1, characterized in that the air supply hole (21) is inclined outwardly in a direction away from the booster impeller body (1).
3. The cold air pre-rotation booster air supply system according to claim 1, characterized in that the tenons (23) are arranged on the turbine blades (3) and are connected with the mortises of the turbine disc (2);
the air supply hole (21) is communicated with the tenon (23).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202211512040.5A CN115853598B (en) | 2022-11-29 | 2022-11-29 | Turbine blade cold air supercharging impeller for axial air intake and pre-rotation supercharging air supply system |
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| CN202211512040.5A CN115853598B (en) | 2022-11-29 | 2022-11-29 | Turbine blade cold air supercharging impeller for axial air intake and pre-rotation supercharging air supply system |
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| CN115853598A CN115853598A (en) | 2023-03-28 |
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| CN116104586A (en) * | 2023-04-11 | 2023-05-12 | 中国航发沈阳发动机研究所 | Locking and fixing structure of turbine rotor blade and turbine disk |
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