CN113898610A - Gas-entraining structure for disk center of rotor disk of compressor - Google Patents
Gas-entraining structure for disk center of rotor disk of compressor Download PDFInfo
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- CN113898610A CN113898610A CN202111178635.7A CN202111178635A CN113898610A CN 113898610 A CN113898610 A CN 113898610A CN 202111178635 A CN202111178635 A CN 202111178635A CN 113898610 A CN113898610 A CN 113898610A
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- 238000000034 method Methods 0.000 description 5
- 239000003638 chemical reducing agent Substances 0.000 description 3
- 238000001816 cooling Methods 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 1
- 230000007717 exclusion Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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Classifications
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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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- Engineering & Computer Science (AREA)
- 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 compressor rotor disk center air entraining design, and particularly relates to an air compressor rotor disk center air entraining structure, which comprises: two stages of rotor discs which are oppositely arranged; the two-stage rotor blades are correspondingly arranged on the outer edge of the first-stage rotor wheel disc; the drum barrel is connected between the two stages of rotor discs and is provided with a plurality of air-entraining holes distributed along the circumferential direction; and the guide cylinder is positioned in the drum and surrounds the disk center part of the two-stage rotor disk, one end of the guide cylinder is connected to the part, close to the outer edge, of the one-stage rotor disk, the other end of the guide cylinder is connected to the part, close to the disk center, of the other-stage rotor disk, and the side wall of the end of the guide cylinder is provided with a plurality of guide holes distributed along the circumferential direction.
Description
Technical Field
The application belongs to the technical field of air entraining design of a disk center of a rotor disk of an air compressor, and particularly relates to an air entraining structure of the disk center of the rotor disk of the air compressor.
Background
When the aero-engine works, gas needs to be led out from the space between the rotor blades of the compressor to the disc center of the rotor disc so as to seal or cool engine parts.
At present, gas is led out from the space between the rotor blades of the compressor to the disk center of the rotor disk, most of the gas holes are arranged on the drum barrel between the adjacent two stages of rotor blades of the compressor, the gas between the two stages of rotor blades is led into the space between the corresponding two stages of rotor disks, and then the gas flows from the disk center to the disk center of the two stages of rotor disks along the radial direction between the two stages of rotor disks and flows out from the disk center, as shown in fig. 1, the scheme for leading out the gas from the space between the rotor blades of the compressor to the disk center of the rotor disk has the following defects:
the gas compressor rotor disk has extremely high rotating speed, gas introduced between the two stages of rotor disks from the gas introducing holes is easy to generate vortex in the process of flowing between the two stages of rotor disks along the radial direction towards the disk center, the existence of the vortex can generate large pressure loss on the gas flowing along the radial direction and block the gas flowing towards the disk center, so that the gas introduced between the two stages of rotor disks from the gas introducing holes is difficult to flow along the radial direction towards the disk center, the gas which can be led out from the disk center part is limited, and the requirements of sealing and cooling engine parts are difficult to meet.
In order to reduce the pressure loss of the gas introduced from the gas guide hole between the two stages of rotor discs and flowing along the radial direction towards the disc center between the two stages of rotor discs, a vortex reducer is often arranged between the two stages of rotor discs, and although the vortex reducer can reduce the pressure loss of the gas flowing along the radial direction towards the disc center between the two stages of rotor discs to a certain extent, the vortex reducer has a complex structure, is difficult to process and assemble, has increased volume and weight, and is easy to generate severe vibration in the starting working process to influence the overall performance of an engine.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
The application aims to provide a bleed air structure for a disk center of a rotor disk of a compressor, so as to overcome or alleviate at least one technical defect of the known existing technology.
The technical scheme of the application is as follows:
a compressor rotor disk heart bleed structure includes:
two stages of rotor discs which are oppositely arranged;
the two-stage rotor blades are correspondingly arranged on the outer edge of the first-stage rotor wheel disc;
the drum barrel is connected between the two stages of rotor discs and is provided with a plurality of air-entraining holes distributed along the circumferential direction;
and the guide cylinder is positioned in the drum and surrounds the disk center part of the two-stage rotor disk, one end of the guide cylinder is connected to the part, close to the outer edge, of the one-stage rotor disk, the other end of the guide cylinder is connected to the part, close to the disk center, of the other-stage rotor disk, and the side wall of the end of the guide cylinder is provided with a plurality of guide holes distributed along the circumferential direction.
According to at least one embodiment of the application, in the air entraining structure for the disk center of the compressor rotor disk, the first-stage rotor disk connected with one end of the guide cylinder at the position close to the outer edge is a rear-stage rotor disk;
the first-stage rotor disk close to the disk center and connected with one end of the guide cylinder is used as a preceding-stage rotor disk.
According to at least one embodiment of the application, in the air entraining structure for the disk center of the compressor rotor disk, the diameter of each flow guide hole gradually shrinks towards the disk center of the two-stage rotor disk.
According to at least one embodiment of the application, in the air entraining structure for the disk center of the compressor rotor disk, one end of the side wall of the guide cylinder, which is provided with the plurality of guide holes, is in interference fit with a corresponding part, close to the disk center, of the rotor disk.
According to at least one embodiment of the application, in the air entraining structure for the disk center of the compressor rotor disk, one end of the side wall of the guide cylinder, which is provided with the plurality of guide holes, is connected with the corresponding part, close to the disk center, of the rotor disk through the bolt.
According to at least one embodiment of the application, in the air entraining structure of the disk center of the rotor disk of the compressor, one end of the side wall of the guide cylinder, which is provided with a plurality of guide holes, is provided with an annular protrusion;
the part, close to the disc center, of the primary rotor wheel disc connected with one end, provided with a plurality of guide holes, of the side wall of the guide cylinder 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 application, in the air entraining structure for the disk center of the compressor rotor disk, the annular convex and the annular connecting edge are convex towards the disk center direction of the two-stage rotor disk.
According to at least one embodiment of the application, in the above-mentioned compressor rotor disk center bleed air structure, the flow guide holes are distributed on the annular protrusion.
According to at least one embodiment of the application, in the air entraining structure of the disk center of the compressor rotor disk, the primary rotor disk connected with one end of the guide shell is integrally formed with the guide shell at a position close to the outer edge.
Drawings
FIG. 1 is a schematic diagram of a current configuration for directing gas from between the rotor blades of a compressor to the center of the disk of a rotor disk;
FIG. 2 is a schematic diagram of a core bleed air structure of a rotor disk of a compressor provided by an embodiment of the application;
wherein:
1-a rotor disk; 2-rotor blades; 3-a drum; 4-a guide cylinder; 5-bolt.
For the purpose of better illustrating the present embodiments, certain engine components of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate 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 when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1-2.
A compressor rotor disk heart bleed structure includes:
the two-stage rotor wheel disc 1 is oppositely arranged;
the two-stage rotor blades 2 are arranged, and each stage of rotor blade 2 is correspondingly arranged on the outer edge of the first-stage rotor disk 1;
the drum barrel 3 is connected between the two stages of rotor discs 1 and is provided with a plurality of air-entraining holes distributed along the circumferential direction;
and the guide cylinder 4 is positioned in the drum barrel 3 and surrounds the disk center part of the two-stage rotor disk 1, one end of the guide cylinder is connected to the part, close to the outer edge, of the one-stage rotor disk 1, the other end of the guide cylinder is connected to the part, close to the disk center, of the other-stage rotor disk 1, and the side wall of the end is provided with a plurality of guide holes distributed along the circumferential direction.
For the disk center air entraining structure of the compressor rotor disk disclosed in the above embodiment, as can be understood by those skilled in the art, air between the two stages of rotor blades 2 can enter between the two stages of rotor disks 1 through the air entraining holes on the drum 3, the air entering between the two stages of rotor disks 1 can impact the outer wall of the guide cylinder 4, flow along the outer wall of the guide cylinder 4, flow to the disk center part of the rotor disk 1 through the guide holes on the outer wall of the guide cylinder 4, and be drawn out from the disk center part of the rotor disk 1 to seal or cool the engine components.
For the disk center air entraining structure of the compressor rotor disk disclosed in the above embodiment, it can be understood by those skilled in the art that the existence of the draft tube 4 between the two-stage rotor disk 1 can destroy the vortex of the air entering between the two-stage rotor disk 1 through the air entraining holes, and reduce the pressure loss of the air flowing between the two-stage rotor disk 1 along the radial direction, in addition, one end of the draft tube 4 is connected to the portion of the one-stage rotor disk 1 near the outer edge, and the other end is connected to the portion of the other-stage rotor disk 1 near the disk center, i.e. one end of the draft tube 4 has a larger diameter, and the other end has a relatively smaller diameter, and the effective cross-sectional area for the air flowing formed between the draft tube 4 and the rotor disk 1 is gradually reduced along the direction of the draft holes, so as to generate a larger pressure difference pushing for the air flowing between the two-stage rotor disk 1 along the radial direction toward the disk center, and each draft hole is distributed at the end of the draft tube 4 connected to the one-stage rotor disk 1 near the disk center, the distance between the two stages of rotor discs 1 is short, pressure loss of gas flowing along the radial direction between the two stages of rotor discs can be further reduced, and therefore the fact that a large amount of gas can be led out from the disc center of the rotor discs 1 can be guaranteed, and sealing and cooling requirements of engine parts are met.
For the air entraining structure of the disk center of the rotor disk of the compressor disclosed in the embodiment, as can be further understood by those skilled in the art, compared with the existing structure of leading the air out from the rotor blades of the compressor to the disk center of the rotor disk, the structure is simple and easy, the volume and the weight are small, and the structure can not seriously affect the overall performance of an engine in the starting process because the guide cylinder 4 is additionally designed.
In some optional embodiments, in the above air entraining structure for the disk center of the compressor rotor disk, the first-stage rotor disk 1 connected to one end of the guide cylinder 4 near the outer edge is a later-stage rotor disk, that is, the end of the guide cylinder 4 with the larger diameter is connected to a part of the later-stage rotor disk near the outer edge;
the first-stage rotor disk 1 which is close to the disk center and connected with one end of the guide cylinder 4 is used as a preceding-stage rotor disk, namely, one end of the guide cylinder 4 with smaller diameter is connected with the part, close to the disk center, of the preceding-stage rotor disk.
For the disk center air entraining structure of the rotor disk of the compressor disclosed by the embodiment, a person skilled in the art can understand that the air between the two stages of rotor blades 2 enters between the two stages of rotor disks 1 through the air entraining holes on the drum 3, the air entering between the two stages of rotor disks 1 has the tendency of flowing towards the rear stage rotor disk due to the existence of inertia, the end with the larger diameter of the guide cylinder 4 is designed to be connected with the part close to the outer edge on the rear stage rotor disk, the end with the smaller diameter is connected with the part close to the disk center on the front stage rotor disk, the air entering between the two stages of rotor disks 1 can effectively impact the outer wall of the guide cylinder 4, the vortex of the air entering between the two stages of rotor disks 1 is damaged, the pressure loss of the air flowing along the radial direction between the two stages of rotor disks 1 can be effectively reduced, the air flows towards the end with the smaller diameter along the outer wall of the guide cylinder 4, the water flows to the disk center part of the rotor disk 1 through the guide hole on the outer wall of the end of the guide cylinder 4 and is led out from the disk center part of the rotor disk 1 in a large amount to seal or cool the engine parts.
In some optional embodiments, in the air entraining structure for the disk center of the compressor rotor disk, the diameter of each flow guide hole gradually shrinks towards the disk center direction of the two-stage rotor disk 1 to form an injection hole, so that a large amount of air entering between the two-stage rotor disk 1 can be injected to the disk center part and is led out from the disk center part, and the sealing and cooling requirements of engine parts are met.
In some optional embodiments, in the air entraining structure for the disk center of the compressor rotor disk, one end of the side wall of the guide cylinder 4, which is provided with the plurality of guide holes, is in interference fit with a corresponding part, which is close to the disk center, of the rotor disk 1, so as to perform centering, reliably transmit torque, and ensure the stability of the structure in the working process of the sending machine.
In some optional embodiments, in the above air bleed structure for the disk center of the compressor rotor disk, one end of the side wall of the guide cylinder 4, which is provided with a plurality of guide holes, is connected to a corresponding portion, which is close to the disk center, of the rotor disk 1 by bolts 5, so as to ensure that one end of the side wall of the guide cylinder 4, which is provided with a plurality of guide holes, is axially connected to the corresponding rotor disk 1.
In some optional embodiments, in the above-mentioned compressor rotor disk core bleed air structure, one end of the side wall of the guide cylinder 4, which is provided with a plurality of guide holes, is provided with an annular protrusion;
the part, close to the disc center, of the primary rotor disc 1 connected with one end, provided with a plurality of guide holes, of the side wall of the guide cylinder 4 is provided with an annular connecting edge;
the annular bulge and the annular connecting edge are connected through a bolt 5.
In some optional embodiments, in the above-mentioned compressor rotor disk center air entraining structure, the annular protruding and annular connecting edge protrudes toward the disk center of the two-stage rotor disk 1.
In some alternative embodiments, in the above-mentioned compressor rotor disk core bleed air structure, the flow guide holes are distributed on the annular protrusion.
In some optional embodiments, in the above-mentioned compressor rotor disk core air entraining structure, the primary rotor disk 1 connected to one end of the guide shell 4 near the outer edge is integrally formed with the guide shell 4.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (9)
1. The utility model provides a compressor rotor disk heart bleed structure which characterized in that includes:
the two-stage rotor wheel disc (1) is oppositely arranged;
the two-stage rotor blade (2), each stage of rotor blade (2) is correspondingly arranged on the outer edge of the rotor wheel disc (1);
the drum barrel (3) is connected between the two stages of the rotor discs (1) and is provided with a plurality of circumferentially distributed air-entraining holes;
and the guide cylinder (4) is positioned in the drum barrel (3) and surrounds the disk center parts of the two stages of rotor disks (1), one end of the guide cylinder is connected to one stage of the rotor disk (1) at a part close to the outer edge, the other end of the guide cylinder is connected to the other stage of the rotor disk (1) at a part close to the disk center, and the side wall of the end is provided with a plurality of guide holes distributed along the circumferential direction.
2. The compressor rotor disk core air entraining structure of claim 1,
a first-stage rotor wheel disc (1) which is close to the outer edge and connected with one end of the guide cylinder (4) is used as a rear-stage rotor wheel disc;
and a first-stage rotor wheel disc (1) which is close to the disc center and connected with one end of the guide cylinder (4) is used as a preceding-stage rotor wheel disc.
3. The compressor rotor disk core air entraining structure of claim 1,
the diameters of the diversion holes gradually shrink towards the center of the two stages of the rotor discs (1).
4. The compressor rotor disk core air entraining structure of claim 1,
one end of the side wall of the guide cylinder (4) provided with a plurality of guide holes is in interference fit with the corresponding part of the rotor wheel disc (1) close to the disc center.
5. The compressor rotor disk core air entraining structure of claim 1,
one end of the side wall of the guide shell (4) provided with a plurality of guide holes is connected with the corresponding part of the rotor disc (1) close to the disc center through a bolt (5).
6. The compressor rotor disk core air entraining structure of claim 5,
one end of the side wall of the guide shell (4) provided with a plurality of guide holes is provided with an annular protrusion;
the part, close to the disc center, of the first-stage rotor disc (1) connected with one end, provided with a plurality of guide holes, of the side wall of the guide cylinder (4) is provided with an annular connecting edge;
the annular bulge and the annular connecting edge are connected through a bolt (5).
7. The compressor rotor disk core air entraining structure of claim 6,
the annular bulge and the annular connecting edge bulge towards the center of the two stages of the rotor discs (1).
8. The compressor rotor disk core air entraining structure of claim 6,
each flow guide hole is distributed on the annular bulge.
9. The compressor rotor disk core air entraining structure of claim 6,
the first-stage rotor wheel disc (1) which is close to the outer edge and connected with one end of the guide shell (4) is integrally formed with the guide shell (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111178635.7A CN113898610A (en) | 2021-10-10 | 2021-10-10 | Gas-entraining structure for disk center of rotor disk of compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111178635.7A CN113898610A (en) | 2021-10-10 | 2021-10-10 | Gas-entraining structure for disk center of rotor disk of compressor |
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| Publication Number | Publication Date |
|---|---|
| CN113898610A true CN113898610A (en) | 2022-01-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111178635.7A Pending CN113898610A (en) | 2021-10-10 | 2021-10-10 | Gas-entraining structure for disk center of rotor disk of compressor |
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2021
- 2021-10-10 CN CN202111178635.7A patent/CN113898610A/en active Pending
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| US4920741A (en) * | 1986-02-28 | 1990-05-01 | Mtu Motoren-Und Turbinen-Union Munchen Gmbh | Apparatus for venting the rotor structure of a compressor of a gas turbine power plant |
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