CN115853598A - Turbine blade air conditioning supercharging impeller with axial air intake and pre-rotation supercharging air supply system - Google Patents
Turbine blade air conditioning supercharging impeller with axial air intake and pre-rotation supercharging air supply system Download PDFInfo
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- CN115853598A CN115853598A CN202211512040.5A CN202211512040A CN115853598A CN 115853598 A CN115853598 A CN 115853598A CN 202211512040 A CN202211512040 A CN 202211512040A CN 115853598 A CN115853598 A CN 115853598A
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Abstract
The invention discloses a turbine blade cold air supercharging impeller with axial air inlet 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 flow channel is arranged in the supercharging impeller body; one side of the supercharging impeller body is provided with an air inlet, and the other side of the supercharging impeller body is provided with an air outlet; the air inlet and the air outlet are both 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 supercharging impeller body rotates. The invention can efficiently carry out cold air pressurization 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 a booster impeller, in particular to a turbine blade cold air booster impeller with axial air inlet and a pre-rotation boosting air supply system.
Background
The cool air boost impeller is an important structure in the turbine structure. In the prior art, various related structures are disclosed, such as a turbine blade cooling air segmented rotating supercharging impeller disclosed in a patent document No. 202011163888.2, a turbine rotor with a cooling bleed air supercharging impeller disclosed in a patent document No. 202010760082.5, a turbine blade cooling air supercharging impeller disclosed in a patent document No. 202011164899.2, a rotating supercharging structure for turbine blade cooling disclosed in a patent document No. 202010756476.3, and the like.
In the structures disclosed in the above patent documents, all the designs are made for the low radius position air intake pre-rotation nozzle, and when the structures are matched with the high radius position air intake pre-rotation nozzle, some of the structures cannot increase the cold air, such as patent documents nos. 202010760082.5 and 202010756476.3; when some of the nozzles are matched with the high-radius air inlet pre-swirl nozzle, the air flow needs to first impact on the booster impeller, then flow radially inwards, finally turn for 180 degrees and then flow radially outwards, so that a large flow loss is caused, and the boosting effect is poor, for example, in patent documents 202011163888.2 and 202011164899.2.
The main reason for the above problems is that the above documents are mostly applied to cool air pressurization of the impeller blades of the high-pressure turbine rotor of the aircraft engine and the gas turbine, and mostly adopt the low-radius position air inlet pre-rotation nozzle. For the cold air pressurization of the impeller blades of the low-pressure turbine rotor, the air inlet pre-rotation nozzle mostly adopts a high-radius air inlet pre-rotation nozzle, and the various structures cannot be adapted to the low-pressure turbine adopting the high-radius air inlet pre-rotation nozzle.
In summary, how to efficiently cool and pressurize the low-pressure turbine rotor provided with the high-radius air inlet pre-rotation nozzle is one of the important problems to be solved urgently in the field.
Disclosure of Invention
The invention aims to provide a turbine blade cold air supercharging impeller with axial air inlet and a pre-rotation supercharging air supply system, which can solve the defects in the prior art and can efficiently carry 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 with axial air inlet, which comprises,
the supercharging impeller comprises a supercharging impeller body, wherein the supercharging impeller body is annular, and a flow channel is arranged in the supercharging impeller body; one side of the supercharging impeller body is provided with an air inlet, and the other side of the supercharging impeller body is provided with an air outlet; the air inlet and the air outlet are both communicated with the flow channel; the air inlet direction of the air inlet is parallel to the axis of the supercharging impeller body;
the impeller blades are arranged in the flow channel and used for driving air to enter from the air inlet and flow outwards along the radial direction when the impeller body rotates.
The turbine blade cold air pressurizing impeller with axial air inlet as described above, wherein optionally, the air inlet is annular, and the number of the impeller blades is multiple;
the impeller blades are distributed in a circumferential array along the direction of the air inlet.
The axial intake turbine blade chilled air impeller as described above, wherein optionally the impeller blades are all inclined in a clockwise direction or all inclined in a counterclockwise direction in a radially outward direction.
The axial intake turbine blade cold air supercharging impeller as described above, wherein optionally the radius of rotation of the outlet port is greater than the radius of rotation of the inlet port.
The turbine blade cold air pressurizing impeller with axial air inlet as described above, wherein optionally, one side of the pressurizing impeller body with the air inlet is provided with a grate ring;
the periphery of the comb tooth ring is provided with comb teeth;
the radius of the grate ring is larger than the rotation radius of the air inlet.
The axial air intake turbine blade cold air supercharging impeller is characterized in that the impeller blade is twisted by the air inlet and extends into the flow passage, so that the direction of the air flow compressed by the impeller blade is changed from axial to radial outward.
The invention also provides a cold air pre-rotation pressurization air supply system, which comprises a turbine disc, a pre-rotation nozzle, turbine blades and the turbine blade cold air pressurization impeller according to any one of the above items;
the turbine blades are mounted at the outer periphery of the turbine disk by tenons;
the turbine disc is provided with an air supply hole, one end of the air supply hole is positioned on the end surface of the turbine disc, and the other end of the air supply hole is positioned at the root part of the mortise of the turbine disc; the air supply hole is used for supplying air to the turbine blade;
the supercharging impeller body is fixedly installed on the turbine disc, and an air outlet in the supercharging impeller body is communicated with the air supply hole.
The cool air pre-swirl supercharging air supply system as described above, wherein optionally, the air supply hole is inclined outward in a direction away from the supercharging impeller body.
The cold air pre-rotation pressurization air supply system is characterized in that the air inlet is opposite to the pre-rotation nozzle.
The cold air pre-rotation pressurization air supply system is characterized in that the tenon is arranged on the turbine blade and is connected with the mortise of the turbine disc;
the air supply hole is communicated with the tenon.
Compared with the prior art, the integrated air inlet supercharging impeller body is arranged, the air inlet of the air inlet supercharging impeller body is directly arranged to be axially air inlet, and the air inlet is right opposite to the pre-rotation nozzle, so that the radial flowing distance of air and the steering direction in the air flowing process are reduced, the flowing loss of the air can be greatly reduced, and the supercharging effect is improved.
Drawings
Fig. 1 is a perspective view of a booster impeller proposed in embodiment 1 of the present invention;
fig. 2 is a perspective view of a booster impeller proposed in 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 of an installation structure of a booster impeller according to embodiment 2 of the present invention.
Description of the reference numerals:
1-a supercharging impeller body, 2-a turbine disc, 3-a turbine blade and 4-a honeycomb structure;
11-air inlet, 12-impeller blade, 13-comb ring, 14-comb;
21-air supply hole, 22-prerotation nozzle and 23-tenon.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
In order to improve the efficient cool air pressurization of the low-pressure turbine rotor of the high-radius air inlet pre-rotation nozzle, the invention provides the following solutions.
Example 1
Referring to fig. 1 to fig. 3, the present embodiment provides an axial intake turbine blade cold air supercharging impeller, wherein: comprising a booster impeller body 1 and impeller blades 12. The booster impeller body 1 is configured to rotate together with the 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 channel is arranged in the supercharging impeller body 1; one side of the supercharging 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. In practice, the air inlet 11 is parallel to the center line of the booster impeller body 1, that is, axial air intake can be realized. Because the prewhirl nozzle is axially discharged, the air inlet 11 is axially arranged and is opposite to the outlet of the prewhirl nozzle, and the air flow resistance can be reduced when the supercharging impeller body 1 is supercharged.
The impeller blades 12 are disposed at the air inlet 11, and the impeller blades 12 are used for driving air into the flow passage when the booster impeller body 1 rotates. In a specific implementation, the air inlet 11 is annular. In specific implementation, the impeller blades 12 are integrally arranged with the additional impeller body 1.
During the concrete implementation, pressure boost impeller body 1 axial admits air, and when gas flows into the runner of pressure boost impeller body 1 by the prewhirl nozzle, because air inlet 11 is just to the prewhirl nozzle, can reduce the energy loss that the gas flows, and then improve the supercharging efficiency. The supercharging impeller provided by the embodiment is particularly suitable for cold air supercharging of low-pressure turbine rotor impeller blades, particularly low-pressure turbines provided with high-radius position air inlet pre-rotation nozzles.
Specifically, the air inlet 11 is annular, and the number of the impeller blades 12 is plural; the impeller blades 12 are distributed in a circumferential array along the direction of the air inlet 11. During implementation, two sides of the air inlet 11 may be provided with flanges to realize axial arrangement of the air inlet 11.
In order to ensure the supercharging effect, the impeller blades 12 are inclined in the clockwise direction or in the counterclockwise direction in the radially outward direction. The inclined direction of the impeller blades 12 is related to the designed rotating direction of the booster impeller body 1, and it is sufficient if the booster impeller body 1 can compress the gas to the flow passage when rotating along with the turbine. More specifically, the impeller blades 12 are twisted by the air inlet 11 and extend into the flow passage, so that the direction of the air flow compressed by the impeller blades 12 is changed from axial to radial outward. That is, the impeller blades 12 are formed by three-dimensional twisted impeller blade instead of the straight impeller blades with equal cross-section, which are used in the prior art. Through the modeling mode of the impeller blades, the axial air inlet of the axial air inlet supercharging impeller 13 is realized, and the air enters the flow channel along the diameter. Meanwhile, the radius of rotation of the air outlet is greater than that of the air inlet 11. Thus, the change of the direction of the airflow can be reduced as much as possible, which is beneficial to reducing the airflow resistance.
In one embodiment, the side of the booster impeller body 1 having the inlet 11 is provided with a grate ring 13, and the grate ring 13 is used to cooperate with the honeycomb structure 4 on other components. The pressurizing impeller body 1, the comb-tooth ring 13 and the fastening structure are integrally designed, so that a single part of the axial air inlet pressurizing impeller can pressurize air conditioning, and is matched with the honeycomb structure 4 to form a comb-tooth sealing structure, and the comb-tooth sealing structure can be conveniently fastened on a turbine disc, so that the number of parts is reduced, and the structural rigidity is improved. More specifically, the grate ring 13 is provided with grate teeth 14 on the periphery; the radius of the grate ring 13 is larger than the radius of rotation of the air inlet 11. More specifically, the grate teeth 14 are annularly arranged along the periphery of the grate ring 13; the number of the grid teeth 14 is at least two.
Example 2
This embodiment is a specific application of embodiment 1, and the same parts are not described again, and only the differences will be described below.
Referring to fig. 4, the present embodiment provides a pre-rotational supercharging air supply system for cool air, which includes a turbine disc 2, turbine blades 3 and a supercharging impeller as disclosed in embodiment 1.
Specifically, the turbine blades 3 are 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 surface of the turbine disc 2, and the other end of which is located at the outer circumferential surface of the turbine disc 2; the air supply hole 21 supplies air into the turbine blade 3. The booster impeller body 1 is fixedly installed on the turbine disc 2, and an air outlet in the booster impeller body 1 is communicated with the air supply hole 21. The air supply hole 21 communicates with the tenon 23. In practical implementation, the air inlet 11 faces the pre-rotation nozzle 22. Furthermore, the turbine blade device further comprises a tenon 23, wherein the tenon 23 is arranged on the turbine blade 3 and is fixedly connected with the turbine disc 2.
In specific use, the gas flows in the following modes: the cooling air flow path is formed by ejecting the cooling air from the pre-swirl nozzle 22, entering the air inlet 11 in the axial direction, passing through the flow path, flowing from the air supply hole 21 to the groove root of the mounting tenon 23, and then flowing into the turbine blade 2 through the radial hole in the tenon 23, thereby finally cooling the turbine blade 2.
In practice, the turbine disk 2 is a disk hub, a web and a disk rim, respectively, from the inside to the outside in the radial direction. An extending arm with a honeycomb structure extends out of the left side of the disc hub and is matched with an external comb tooth ring to form a comb tooth sealing structure. The turbine blades 3 are mounted in the mortises in the rim of the turbine disc 2 by means of tenons 23.
In practical implementation, the air supply hole 21 is inclined outwards in a direction away from the booster impeller body 1. So arranged, it can be advantageous to reduce the resistance of the air flow when passing through the air supply holes 21.
With the above configuration, the arrangement of the booster impeller and the effect of high-efficiency, low-loss pressurization of the cooling air when the pre-swirl nozzle 22 is at a higher radius position can be achieved. Specifically, the integrated air inlet supercharging impeller body is arranged, the air inlet of the air inlet supercharging impeller body is directly arranged to be axially air inlet, and the air inlet is over against the pre-rotation nozzle, so that the radial flowing distance of air and the steering direction in the air flowing process are reduced, the flowing loss of the air can be greatly reduced, and the supercharging effect is improved.
The construction, features and functions of the present invention are described in detail in the embodiments illustrated in the drawings, which are only preferred embodiments of the present invention, but the present invention is not limited by the scope of the drawings, and all equivalent embodiments modified or modified according to the concept of the present invention should be within the scope of the present invention without departing from the spirit of the present invention covered by the description and the drawings.
Claims (10)
1. The utility model provides an axial turbine blade air conditioning impeller that admits air which characterized in that: comprises the steps of (a) preparing a mixture of a plurality of raw materials,
the impeller comprises a booster impeller body (1), wherein the booster impeller body (1) is annular, and a flow channel is arranged in the booster impeller body (1); one side of the supercharging 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; the air inlet direction of the air inlet (11) is parallel to the axis of the supercharging impeller body (1);
impeller blades (12), the impeller blades (12) are arranged in the flow channel, and the blades (13) are used for driving air to enter from the air inlet (11) and flow outwards in the radial direction when the impeller body (1) rotates.
2. The axial intake, turbine blade chilled air impeller of claim 1, wherein: the air inlet (11) is annular, and the number of the impeller blades (12) is multiple;
the impeller blades (12) are distributed in a circumferential array along the direction of the air inlet (11).
3. The axial intake, turbine blade chilled air impeller of claim 2, wherein: the impeller blades (12) are inclined towards the clockwise direction or towards the anticlockwise direction along the radial outward direction.
4. The axial intake, turbine blade chilled air impeller of claim 1, wherein: the radius of rotation of the air outlet is greater than the radius of rotation of the air inlet (11).
5. The axial intake, turbine blade chilled air impeller of claim 1, wherein: a comb-tooth ring (13) is arranged on one side of the supercharging impeller body (1) with the air inlet (11);
the periphery of the grate ring (13) is provided with grate teeth (14);
the radius of the grate ring (13) is larger than the rotation radius of the air inlet (11).
6. The axial intake, turbine blade chilled air impeller of claim 5, wherein: the impeller blades (12) are twisted from the air inlet (11) and extend into the flow channel, so that the direction of the air flow compressed by the impeller blades (12) is changed from axial direction to radial direction.
7. A chilled air pre-swirl boost air supply system, characterized by comprising a turbine disc (2), pre-swirl nozzles, turbine blades (3) and a turbine blade chilled air boost impeller according to any of claims 1-6;
the turbine blades (3) are mounted at the outer 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 located on the end face of the turbine disc (2), and the other end of the air supply hole is located at the root of the mortise 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 installed on the turbine disc (2), and the air outlet on the supercharging impeller body (1) is communicated with the air supply hole (21).
8. The pre-swirl cool air supply system according to claim 7, wherein the air supply hole (21) is inclined outwardly in a direction away from the booster impeller body (1).
9. Cold air pre-swirl supercharging air supply system according to claim 7, characterized in that the air inlet (11) is directly opposite the pre-swirl nozzle (22).
10. The chilled air pre-swirl boost air supply system according to claim 7, characterized in that the tenon (23) is provided on the turbine blade (3) and is connected with the mortise of the turbine disc (2);
the air supply hole (21) is communicated with the tenon (23).
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| 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 true CN115853598A (en) | 2023-03-28 |
| CN115853598B CN115853598B (en) | 2023-09-22 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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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