CN113847280B - Interstage air entraining structure of compressor rotor - Google Patents
Interstage air entraining structure of compressor rotor Download PDFInfo
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- CN113847280B CN113847280B CN202111184325.6A CN202111184325A CN113847280B CN 113847280 B CN113847280 B CN 113847280B CN 202111184325 A CN202111184325 A CN 202111184325A CN 113847280 B CN113847280 B CN 113847280B
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- rotor
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- guide cylinder
- wheel disc
- rotor wheel
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
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- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The application belongs to the technical field of air entraining design of air compressor rotors, and particularly relates to an interstage air entraining structure of an air compressor rotor, which comprises two stages of rotor wheel discs which are oppositely arranged; two-stage rotor blades, wherein each stage of rotor blade is correspondingly arranged at the outer edge of the first-stage rotor wheel disc; a drum connected between the two stages of rotor disks, and having a plurality of circumferentially distributed air introduction holes thereon; the guide cylinder is positioned in the drum cylinder and surrounds the disk center of the two-stage rotor disk, one end of the guide cylinder is connected to the position, close to the outer edge, of the one-stage rotor disk, and the other end of the guide cylinder is connected to the position, close to the disk center, of the other-stage rotor disk, and the positions are meshed through the arc end teeth.
Description
Technical Field
The application belongs to the technical field of compressor rotor bleed air design, and particularly relates to an interstage bleed air structure of a compressor rotor.
Background
When the aeroengine works, gas is led out from the space between the rotor blades of the compressor to the disk center of the rotor disk, so that engine components can be sealed or cooled.
At present, gas is led out from the rotor blades of the compressor to the center of the rotor wheel disc, and a gas-leading hole is formed in a drum barrel between two adjacent stages of rotor blades of the compressor, so that the gas between the two stages of rotor blades is led into the space between the corresponding two stages of rotor wheel discs, then flows along the radial direction of the center of the two stages of rotor wheel discs between the two stages of rotor wheel discs, and flows out from the center of the rotor wheel disc, as shown in fig. 1, the scheme for leading out the gas from the space between the rotor blades of the compressor to the center of the rotor wheel disc has the following defects:
the compressor rotor disk has extremely high rotational speed, and the gas between the two-stage rotor disk is introduced from the bleed hole, and in the radial direction of disk center direction flow between the two-stage rotor disk, very easily produces the vortex, and the existence of this kind of vortex can produce great pressure loss to the radial flow of gas, obstructs the gas to disk center direction flow, causes the gas that introduces between the two-stage rotor disk from the bleed hole, is difficult to flow along radial direction to disk center direction, and the gas that can draw forth in disk center position is limited, is difficult to satisfy engine parts and seals and the demand of cooling thereof.
In order to reduce the pressure loss caused by introducing gas from the bleed holes between the two-stage rotor disks and flowing along the radial direction of the disk center between the two-stage rotor disks, a vortex reducer is arranged between the two-stage rotor disks, and the vortex reducer can reduce the pressure loss caused by the gas flowing along the radial direction of the disk center between the two-stage rotor disks to a certain extent, but has a complex structure, is difficult to process and assemble, has increased volume and weight, is easy to generate severe vibration in the starting working process, and affects the integral performance of the engine.
The present application has been made in view of the above-described technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present application, which is not necessarily prior art to the present patent application, and should not be used for evaluating the novelty and creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide a compressor rotor interstage bleed air structure that overcomes or mitigates at least one of the known technical disadvantages.
The technical scheme of the application is as follows:
An interstage bleed air structure of a compressor rotor, comprising
Two stages of rotor wheel discs are oppositely arranged;
Two-stage rotor blades, wherein each stage of rotor blade is correspondingly arranged at the outer edge of the first-stage rotor wheel disc;
a drum connected between the two stages of rotor disks, and having a plurality of circumferentially distributed air introduction holes thereon;
The guide cylinder is positioned in the drum cylinder and surrounds the disk center of the two-stage rotor disk, one end of the guide cylinder is connected to the position, close to the outer edge, of the one-stage rotor disk, and the other end of the guide cylinder is connected to the position, close to the disk center, of the other-stage rotor disk, and the positions are meshed through the arc end teeth.
According to at least one embodiment of the present application, in the above-mentioned air bleed structure between the compressor rotor stages, the first-stage rotor disk, which is close to the outer edge portion and is connected to one end of the guide cylinder, is the subsequent-stage rotor disk;
The primary rotor disk which is close to the disk center and meshed with one end of the guide cylinder through the arc end teeth is the front rotor disk.
According to at least one embodiment of the present application, in the above-mentioned air bleed structure between the compressor rotor stages, the guide cylinder is integrally formed between one end of the rear rotor disk and the rear rotor disk.
According to at least one embodiment of the present application, in the above-mentioned air bleed structure between the compressor rotor stages, the guide cylinder is centered by the spigot between the end of the guide cylinder facing the front stage rotor disk and the circular arc end tooth side wall between the front stage rotor disks.
According to at least one embodiment of the present application, in the above-mentioned air bleed structure between the compressor rotor stages, the guide cylinder is connected by bolts to one end of the front rotor disk facing the front rotor disk.
According to at least one embodiment of the present application, in the above-mentioned air bleed structure between stages of a compressor rotor, one end of the guide cylinder facing the front stage rotor disk has an annular protrusion;
the part of the front-stage rotor wheel disc, which is close to the disc center, is provided with an annular connecting edge;
The annular bulge and the annular connecting edge are connected through bolts.
According to at least one embodiment of the present application, in the above-mentioned air bleed structure between the compressor rotor stages, the annular protrusion and the annular connecting edge protrude toward the center of the two-stage rotor disk.
Drawings
FIG. 1 is a schematic illustration of a current configuration for extracting gas from between compressor rotor blades toward a rotor disk core;
FIG. 2 is a schematic illustration of a compressor rotor interstage bleed air configuration provided by an embodiment of the present application;
FIG. 3 is a partial view in the direction A of FIG. 2;
FIG. 4 is a B-B cross-sectional view of FIG. 3;
Wherein:
1-a rotor disk; 2-rotor blades; 3-drum; 4-a guide cylinder; 5-bolts.
For the purpose of better illustrating the embodiments, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the actual product dimensions; further, the drawings are for illustrative purposes, wherein the terms describing the positional relationship are limited to the illustrative description only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solution of the present application and its advantages more clear, the technical solution of the present application will be further and completely described in detail with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application and not for limitation of the present application. It should be noted that, for convenience of description, only the part related to the present application is shown in the drawings, and other related parts may refer to the general design, and the embodiments of the present application and the technical features of the embodiments may be combined with each other to obtain new embodiments without conflict.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of the application should be given the ordinary meaning as understood by one of ordinary skill in the art to which the application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in the description of the present application are merely used for indicating relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and that the relative positional relationships may be changed when the absolute position of the object to be described is changed, thus not being construed as limiting the application. The terms "first," "second," "third," and the like, as used in the description of the present application, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the application are not to be construed as limiting the amount absolutely, but rather as existence of at least one. As used in this description of the application, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term as such, but does not exclude other elements or articles from the list of elements or articles that appear after the term.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description of the present application are used in a broad sense, and for example, the connection may be a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The application is described in further detail below with reference to fig. 1 to 4.
An interstage bleed air structure of a compressor rotor, comprising
Two-stage rotor wheel discs 1 are oppositely arranged;
two stages of rotor blades 2, wherein each stage of rotor blade 2 is correspondingly arranged at the outer edge of the first-stage rotor wheel disc 1;
a drum 3 connected between the two-stage rotor disks 1 and having a plurality of circumferentially distributed air introduction holes thereon;
The guide cylinder 4 is positioned in the drum cylinder 3 and surrounds the disk center of the two-stage rotor disk 1, one end of the guide cylinder is connected to the position, close to the outer edge, of the one-stage rotor disk 1, and the other end of the guide cylinder is connected to the position, close to the disk center, of the other-stage rotor disk 1 and meshed through the arc end teeth.
For the air bleed structure between the stages of the compressor rotor disclosed in the above embodiment, it will be understood by those skilled in the art that the air between the two stages of rotor blades 2 can enter between the two stages of rotor discs 1 through the air bleed holes on the drum 3, the air entering between the two stages of rotor discs 1 can impact the outer wall of the guide cylinder 4, flow along the outer wall of the guide cylinder 4, flow to the center part of the rotor disc 1 through the gap between the guide cylinder 4 and the tooth tops of the arc end teeth of the rotor disc 1, be led out from the center part of the rotor disc 1, and be supplied to seal or cool engine components.
For the compressor rotor interstage bleed air structure disclosed in the above embodiment, it can be understood by those skilled in the art that the existence of the guide cylinder 4 between the two-stage rotor wheel discs 1 can destroy the vortex of the gas entering between the two-stage rotor wheel discs 1 through the air guiding holes, reduce the pressure loss of the gas flowing along the radial direction between the two-stage rotor wheel discs 1, in addition, one end of the guide cylinder 4 is connected to the part of the one-stage rotor wheel disc 1 close to the outer edge, the other end is connected to the part of the other-stage rotor wheel disc 1 close to the center, that is, one end of the guide cylinder 4 has a larger diameter, the other end has a smaller diameter, and the effective sectional area of the gas flowing between the guide cylinder 4 and the rotor wheel disc 1 is gradually reduced in the direction of the air guiding holes, so that a larger pressure difference pushing can be generated for the gas flowing along the radial direction between the two-stage rotor wheel discs 1 and the center part of the corresponding stage rotor wheel disc 1, and the gap between the smaller end of the guide cylinder 4 and the circular arc tooth top of the corresponding stage rotor wheel disc 1 can be further reduced, and the pressure loss of the gas flowing along the radial direction between the two-stage rotor wheel discs 1 can be further reduced, and a larger amount of gas can be led out from the center of the rotor disc 1 to the center of the rotor disc to meet the requirements of the engine and the sealing parts.
For the air bleed structure between the stages of the compressor rotor disclosed in the above embodiment, it can be understood by those skilled in the art that, compared with the existing air bleed structure from the space between the rotor blades of the compressor to the disk center of the rotor disk, only the guide cylinder 4 is added, and the air bleed structure is simple and easy in structure, small in size and weight, and does not seriously affect the overall performance of the engine during the starting operation.
For the compressor rotor interstage bleed air structure disclosed in the above embodiment, those skilled in the art can also understand that the smaller diameter end of the guide cylinder 4 is meshed with the corresponding stage rotor disk 1 through the arc end teeth, so that a gap for gas to flow from the two stages of rotor disks 1 to the disk center part is formed, reliable torque transmission is also realized, and the stability of the structure can be ensured in the working process of the transmitter.
In some alternative embodiments, in the above-mentioned air bleed structure between the stages of the compressor rotor, the first-stage rotor disk 1 connected to one end of the guide cylinder 4 is a rear-stage rotor disk, that is, the end of the guide cylinder 4 with a larger diameter is connected to the position of the rear-stage rotor disk near the outer edge;
The first-stage rotor wheel disc 1 which is close to the disc center and meshed with one end of the guide cylinder 4 through the arc end teeth is a front-stage rotor wheel disc, namely, one end of the guide cylinder 4 with smaller diameter is connected to the part of the front-stage rotor wheel disc close to the disc center.
As can be appreciated by those skilled in the art, with the air bleed structure between the stages of the compressor rotor disclosed in the above embodiment, the air between the two stages of rotor blades 2 enters between the two stages of rotor disks 1 through the air bleed holes on the drum 3, the air entering between the two stages of rotor disks 1 has a tendency to flow to the rotor disks of the rear stage due to inertia, the end with the larger diameter of the guide cylinder 4 is designed to be connected to the position on the rotor disks of the rear stage close to the outer edge, the end with the smaller diameter is meshed with the position on the rotor disks of the front stage close to the center through the circular arc end teeth, the air entering between the two stages of rotor disks 1 can effectively impact the outer wall of the guide cylinder 4, so that the vortex of the air entering between the two stages of rotor disks 1 is broken, the pressure loss of the air flowing between the two stages of rotor disks 1 along the radial direction can be effectively reduced, the air flowing along the outer wall of the guide cylinder 4 towards the center of the rotor disks 1 through the gap between the end of the guide cylinder 4 and the circular arc end tooth tip of the front stage of the rotor disk, and the center of the rotor disk 1 is largely led out, and the center of the rotor disk 1 is supplied for sealing or cooling of engine components.
In some alternative embodiments, in the above-mentioned compressor rotor interstage bleed air structure, the guide cylinder 4 is integrally formed between one end of the rear-stage rotor disk and the rear-stage rotor disk.
In some alternative embodiments, in the above-mentioned air bleed structure between the stages of the compressor rotor, the guide cylinder 4 is oriented between one end of the front stage rotor wheel disc and the side wall of the circular arc end tooth between the front stage rotor wheel discs, and is centered by the rabbet, so as to facilitate assembly and ensure the stability of the structure during the working process of the engine
In some alternative embodiments, in the above-mentioned air bleed structure between the stages of the compressor rotor, the guide cylinder 4 is connected between one end of the preceding stage rotor disk and the preceding stage rotor disk by bolts 5, so that the smaller diameter end of the guide cylinder 4 is ensured to be axially connected with the preceding stage rotor disk.
In some alternative embodiments, in the above-described compressor rotor interstage bleed air structure, the end of the guide cylinder 4 facing the preceding rotor disk has an annular projection;
the part of the front-stage rotor wheel disc, which is close to the disc center, is provided with an annular connecting edge;
The annular bulge and the annular connecting edge are connected through bolts 5.
In some alternative embodiments, in the above-described compressor rotor interstage bleed air structure, the annular projection, the annular connecting edge, projects in the direction of the hub of the two-stage rotor disk 1.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments shown in the drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the related technical features without departing from the principle of the present application, and those changes or substitutions will fall within the scope of the present application.
Claims (7)
1. An interstage bleed air structure of a compressor rotor, comprising
Two-stage rotor wheel discs (1) are oppositely arranged;
two stages of rotor blades (2), wherein each stage of rotor blades (2) is correspondingly arranged on the outer edge of the rotor wheel disc (1) of one stage;
A drum (3) connected between the two stages of rotor disks (1) and provided with a plurality of circumferentially distributed air-introducing holes;
The guide cylinder (4) is positioned in the drum cylinder (3), surrounds the center part of the rotor wheel disc (1) at two stages, one end of the guide cylinder is connected to the part, close to the outer edge, of the rotor wheel disc (1) at one stage, the end of the guide cylinder is provided with a larger diameter, the other end of the guide cylinder is provided with a smaller diameter, the guide cylinder is connected to the part, close to the center, of the rotor wheel disc (1) at the other stage, the guide cylinder is meshed with the rotor wheel disc (1) through arc end teeth, a gap is formed between the guide cylinder (4) and the rotor wheel disc (1), and the effective sectional area of the gas flow formed between the guide cylinder and the rotor wheel disc (1) is gradually reduced in the direction of guide flow.
2. The compressor rotor interstage bleed air structure of claim 1, wherein,
A first-stage rotor wheel disc (1) which is close to the outer edge part and is connected with one end of the guide cylinder (4) is a rear-stage rotor wheel disc;
The primary rotor wheel disc (1) which is close to the disc center and meshed with one end of the guide cylinder (4) through the arc end teeth is used as a front rotor wheel disc.
3. The compressor rotor interstage bleed air structure of claim 2, wherein,
And the guide cylinder (4) faces one end of the rear-stage rotor wheel disc and is integrally formed between the rear-stage rotor wheel discs.
4. The compressor rotor interstage bleed air structure of claim 2, wherein,
And the guide cylinder (4) faces to the space between one end of the front-stage rotor wheel disc and the side wall of the arc end tooth between the front-stage rotor wheel discs and is centered through the spigot.
5. The compressor rotor interstage bleed air structure of claim 2, wherein,
The guide cylinder (4) faces one end of the front-stage rotor wheel disc and is connected with the front-stage rotor wheel disc through bolts (5).
6. The compressor rotor interstage bleed air structure of claim 5, wherein,
One end of the guide cylinder (4) facing the front-stage rotor wheel disc is provided with an annular bulge;
The front-stage rotor wheel disc is provided with an annular connecting edge at a position close to the disc center;
The annular bulge and the annular connecting edge are connected through bolts (5).
7. The compressor rotor interstage bleed air structure of claim 6, wherein,
The annular bulge and the annular connecting edge bulge towards the direction of the center of the two-stage rotor wheel disc (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111184325.6A CN113847280B (en) | 2021-10-10 | 2021-10-10 | Interstage air entraining structure of compressor rotor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111184325.6A CN113847280B (en) | 2021-10-10 | 2021-10-10 | Interstage air entraining structure of compressor rotor |
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| CN113847280A CN113847280A (en) | 2021-12-28 |
| CN113847280B true CN113847280B (en) | 2024-08-02 |
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