CN111878450A - Sealing mechanism, axial flow compressor and gas turbine - Google Patents
Sealing mechanism, axial flow compressor and gas turbine Download PDFInfo
- Publication number
- CN111878450A CN111878450A CN202010803791.7A CN202010803791A CN111878450A CN 111878450 A CN111878450 A CN 111878450A CN 202010803791 A CN202010803791 A CN 202010803791A CN 111878450 A CN111878450 A CN 111878450A
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- sealing
- inner hub
- arresting
- blades
- obturating
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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
- F04D29/08—Sealings
- F04D29/083—Sealings especially adapted for elastic fluid pumps
Abstract
The invention discloses a sealing mechanism, an axial flow compressor and a gas turbine. This mechanism of obturating includes stator blade, interior hub and the subassembly of obturating, and the subassembly of obturating is located between stator blade's inner ring and the interior hub, and wherein, the subassembly of obturating sets up on interior hub, and the subassembly of obturating is located the place ahead of the labyrinth of obturating to the leakage flow of working medium, and the subassembly of obturating can rotate in order to offset the pressure energy of the working medium of flowing to the subassembly of obturating along with the rotation of interior hub. According to the sealing mechanism, the working medium leaked between the stator blade inner ring and the inner hub flows to the sealing assembly, and due to the fact that centrifugal force exists in the sealing assembly along with the rotation of the inner hub, the sealing assembly does work on the leakage flow to offset the pressure energy of the leakage flow, the leakage flow flowing to the front of the sealing labyrinth is reduced, the static pressure in the front of the sealing labyrinth is greatly reduced, the pressure difference in the front of and behind the sealing labyrinth is greatly reduced, the leakage flow is reduced, and the efficiency loss of the axial flow compressor is reduced.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a sealing mechanism, an axial flow compressor and a gas turbine.
Background
The gas turbine is a rotary power machine which takes continuously flowing gas as a working medium and converts heat energy into mechanical work, and generally comprises three parts, namely a gas compressor, a combustion chamber and a gas turbine. Among them, the commonly used compressors are a centrifugal compressor and an axial compressor.
An axial compressor is an impeller machine for converting mechanical energy into pressure potential energy. An axial compressor generally includes an outer casing, an inner hub, and a plurality of stages of blades, each stage of blades including a row of rotor blades and a row of stator blades in a front-to-back order. The stator blades are fixed on the outer casing, the rotor blades are installed on the inner hub, and the inner hub is connected with the power mechanism. Since the rotor blades and the inner hub are rotating parts and the stator blades are non-rotating parts, a gap necessarily exists between the rotor and the stator, and the gap exists between the stator blade inner ring and the inner hub. Working media such as air enter the axial flow self-compressor, after the working media enter the rotor blades at a proper angle, the total pressure is increased, the static pressure is increased, mechanical energy is converted into pressure potential energy and kinetic energy, then air flow enters the stator blades, the static pressure rises, and the multistage blades are repeated to play a role in pressurization. Because the airflow pressure behind the stator blade is higher than that in front of the stator blade and the gap exists, the leakage flow exists in the gap between the front and the rear of the inner ring of the stator blade, which causes the efficiency loss of the axial flow compressor.
In order to reduce the leakage flow of the axial compressor, a sealing labyrinth is usually added at the leakage position. However, because the sealing effect of the sealing labyrinth is limited, the pressure difference between the front and the rear of the sealing labyrinth is still large, even if the sealing labyrinth is used, the flow loss of the axial-flow compressor is still high, a large part of the acted gas flows through the sealing labyrinth and leaks to the atmosphere, and the efficiency loss of the axial-flow compressor is still large.
Disclosure of Invention
The embodiment of the invention provides a sealing mechanism, an axial flow compressor and a gas turbine, and solves the problem of large efficiency loss of the axial flow compressor.
On one hand, the embodiment of the invention provides a sealing mechanism which comprises a stator blade, an inner hub and a sealing assembly, wherein the sealing assembly is positioned between an inner ring of the stator blade and the inner hub, the sealing assembly is arranged on the inner hub, the sealing assembly is positioned in front of a sealing labyrinth in the leakage flow direction of a working medium, and the sealing assembly can rotate along with the rotation of the inner hub to counteract the pressure energy of the working medium flowing to the sealing assembly.
According to one aspect of an embodiment of the invention, the packing assembly includes a plurality of arresting blades disposed on the inner hub around a circumference thereof.
According to an aspect of an embodiment of the present invention, the blocking vane is provided with a first end and a second end in sequence in an upward direction of a leakage flow of the working medium; in the circumference of inner hub, the second end of a plurality of arresting blades is the form setting of gathering together, and the first end of a plurality of arresting blades is radial setting.
According to an aspect of an embodiment of the invention, the spacing between the second ends of adjacent arresting blades is the same.
According to an aspect of an embodiment of the invention, the first ends of adjacent arresting blades are equally spaced.
According to an aspect of an embodiment of the invention, the plurality of arresting blades are arranged on a same cross section perpendicular to the inner hub rotation axis.
According to an aspect of an embodiment of the invention, the arresting blades are arranged obliquely with respect to the direction of the axis of rotation of the inner hub.
According to an aspect of an embodiment of the invention, the direction of inflow of the working fluid from the gap between adjacent arresting blades is opposite to the direction of rotation of the inner hub.
On the other hand, the embodiment of the invention provides an axial flow compressor, which comprises the sealing mechanism.
In another aspect, an embodiment of the present invention provides a gas turbine including the axial compressor as described above.
According to the sealing mechanism provided by the embodiment of the invention, part of working medium passes through the rotor blade and the edge plate of the stator blade from the main flow and leaks into the containing cavity to form leakage flow, because the sealing assembly has centrifugal force along with the rotation of the inner hub, the sealing assembly works on the leakage flow, the pressure of the leakage flow can be counteracted by the centrifugal force, the flow speed of the leakage flow is reduced, the flow of the leakage flow entering the containing cavity is reduced, so that the leakage flow flowing to the front of the sealing labyrinth is also reduced, the static pressure in the front of the sealing labyrinth is greatly reduced, the pressure difference in the front of the sealing labyrinth and the back of the sealing labyrinth is greatly reduced, the sealing effect is further improved, the leakage flow is reduced, the efficiency loss of the axial flow compressor is reduced, and the efficiency of the.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
Fig. 1 is a schematic cross-sectional structural view of a sealing mechanism according to an embodiment of the present invention.
Fig. 2 is a left side view of the inner hub of the sealing mechanism according to the embodiment of the present invention.
In the drawings:
100-inner hub, 200-stator blade inner ring, 300-sealing labyrinth, 400-sealing component, 500-rotor blade, 600-stator blade;
410-arresting leaves;
411-first end, 412-second end.
Detailed Description
The embodiments of the present invention will be described in further detail with reference to the drawings and examples. The following detailed description of the embodiments and the accompanying drawings are provided to illustrate the principles of the invention and are not intended to limit the scope of the invention, i.e., the invention is not limited to the described embodiments.
In the description of the present invention, it is to be noted that, unless otherwise specified, the terms "first" and "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance; "plurality" means two or more; the terms "inner", "outer", "top", "bottom", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience in describing the present invention and simplifying the description, but do not indicate or imply that the referred devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
Referring to fig. 1, the sealing mechanism according to the embodiment of the present invention includes a stator blade inner ring 200, an inner hub 100, and a sealing assembly 400, where the sealing assembly 400 is disposed between the stator blade inner ring 200 and the inner hub 100, the sealing assembly 400 is disposed on the inner hub 100, the sealing assembly 400 is located in front of the sealing labyrinth 300 in the leakage flow direction of the working medium, and the sealing assembly 400 can rotate along with the rotation of the inner hub 100 to counteract the pressure energy of the working medium flowing to the sealing assembly 400. In the axial flow compressor in the prior art, a gap exists between the stator blade inner ring 200 and the inner hub 100, and a cavity-shaped space existing near the gap is called as a cavity. Part of working medium of the embodiment passes through the edge plates of the rotor blade 500 and the stator blade 600 by main flow, leaks and enters the cavity to become leakage flow, because the sealing assembly 400 rotates along with the inner hub 100 and has centrifugal force, the sealing assembly 400 does work on the leakage flow, the pressure of the leakage flow can be counteracted by the centrifugal force, the flow speed of the leakage flow is reduced, the flow of the leakage flow entering the cavity is reduced, so that the leakage flow flowing to the front of the sealing labyrinth 300 is also reduced, the static pressure in the front of the sealing labyrinth 300 is greatly reduced, the pressure difference in the front of and behind the sealing labyrinth 300 is greatly reduced, the sealing effect is improved, the leakage flow is reduced, the efficiency loss of the axial flow compressor is effectively reduced, and the efficiency of the axial flow of the compressor is improved.
Referring to fig. 2, as an alternative embodiment, the packing assembly 400 includes a plurality of arresting blades 410, and the plurality of arresting blades 410 are disposed on the inner hub 100 around the circumference of the inner hub 100.
The plurality of barrier blades 410 of the present embodiment form a ring structure around the circumference of the inner hub 100, and the ring structure is disposed on the inner hub 100.
Specifically, a plurality of arresting blades 410 are provided at the intersection of the inner hub 100 and the rotor disc for providing the rotor blades 500; the number of the arresting blades 410 is plural, and the specific number can be determined according to specific parameters of the axial compressor.
As an alternative embodiment, in the direction of the leakage flow of the working medium, the arresting blade 410 is provided with a first end 411 and a second end 412 in sequence; in the circumferential direction of the inner hub 100, the second ends 412 of the plurality of barrier blades 410 are arranged in a converging manner, and the first ends 411 of the plurality of barrier blades 410 are arranged in a radial manner.
The plurality of blocking blades 410 of the present embodiment converge in the leakage flow direction of the working medium, and the distance between the plurality of blocking blades 410 is narrowed or joined by widening, that is, the second ends 412 of the plurality of blocking blades 410 have a distance therebetween, or the second ends 412 of the plurality of blocking blades 410 are joined to each other.
The structure of the arresting blade 410 is not limited, and the arresting blade 410 may be planar, curved, and the like, including simple wedge, thin sheet, and complex blade shape, and can realize the circumferential movement of the trapped working medium along the inner hub 100.
Also, the radial height of the arresting blades 410 is not particularly limited, but should be such that they do negative work on the working fluid without interfering with the normal operation of other components.
As an alternative embodiment, the second ends 412 of adjacent arresting vanes 410 are equally spaced; the first ends 411 of adjacent arresting blades 410 are equally spaced.
The arresting blades 410 of the present embodiment are uniformly distributed along the circumferential direction of the inner hub 100, and uniformly apply negative work to the working medium in the circumferential direction of the inner hub 100.
As an alternative embodiment, a plurality of arresting blades 410 are arranged on the same cross section perpendicular to the rotation axis of the inner hub 100.
A plurality of blades 410 of arresting of this embodiment distribute on same radial cross section of inner hub 100, can drive working medium and concentrate in a certain radial cross section scope of inner hub 100 and form the whirl protective screen, when having more job stabilization nature, can promote the effect of doing the negative work to the working medium, and then promote the seal pressure effect, reduce to reveal and flow.
As an alternative embodiment, the arresting blades 410 are arranged obliquely with respect to the direction of the axis of rotation of the inner hub 100.
In the present embodiment, the variation of the width of the spacing between the blocking blades 410 is achieved by the inclination angle of the blocking blades 410, and the spacing between the blocking blades 410 is changed from wide to narrow in the leakage flow direction of the working medium, so that the working medium can be entrained to move along the circumferential direction of the inner hub 100, and a rotational flow barrier is formed.
It should be noted that, the installation angle of the specific arresting blade 410 is not limited, but it is required to ensure that the working medium can work along the circumferential direction of the inner hub 100, the circumferential speed of the working medium is increased, and the centrifugal force applied to the working medium is enhanced.
As an alternative embodiment, the flowing direction of the working medium from the gap between the adjacent arresting blades 410 is opposite to the rotation direction of the inner hub 100, so that the working medium can be effectively driven to move along the circumferential direction of the inner hub 100.
In the present embodiment, in the leakage flow direction of the working medium, the arresting blade 410 has a first end 411 and a second end 412 in sequence, and the second end 412 of the arresting blade 410 is inclined against the rotation direction of the inner hub 100, which can also be understood as that the first end 411 of the arresting blade 410 is inclined towards the rotation direction of the inner hub 100, that is, the direction of the working medium flowing to the gap between the adjacent arresting blades 410 is opposite to the rotation direction of the inner hub 100.
On the whole, the sealing mechanism of this embodiment, under the effect of the centrifugal force that the subassembly 400 of obturating exerted, the working medium forms the whirl in the circumference of subassembly 400 of obturating, reduces the working medium that gets into the appearance chamber between the rotor and the stator, realizes reducing the static pressure before the labyrinth 300 for the differential pressure before and after the labyrinth 300 obtains reducing by a wide margin, promotes the effect of obturating, reduces and reveals the flow, reduces axial compressor's efficiency loss, improves axial compressor's efficiency.
The embodiment of the invention also provides an axial flow compressor which comprises the sealing mechanism in the embodiment.
In the embodiment, the pressure of the working medium, such as air, is greatly increased after the working medium enters the axial flow compressor, due to the arrangement of the sealing mechanism in the embodiment, a very small part of gas leaks through a gap between the stator blade inner ring 200 and the inner hub 100, and most of gas flows out of the axial flow compressor, so that the efficiency loss of the axial flow compressor is small.
The embodiment of the invention also provides a gas turbine which comprises the axial-flow compressor of the embodiment, the efficiency of the axial-flow compressor is higher, and the overall efficiency of the gas turbine is also improved.
It should be understood by those skilled in the art that the foregoing is only illustrative of the present invention, and the scope of the present invention is not limited thereto. It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (10)
1. A sealing mechanism, comprising a stator blade, an inner hub, and a sealing assembly located between an inner ring of the stator blade and the inner hub, wherein,
the sealing assembly is arranged on the inner hub, the sealing assembly is located in front of the sealing labyrinth in the leakage flow direction of the working medium, and the sealing assembly can rotate along with the rotation of the inner hub to offset the pressure energy of the working medium flowing to the sealing assembly.
2. The seal mechanism of claim 1, wherein the seal assembly includes a plurality of arresting blades disposed about a circumference of the inner hub.
3. The seal mechanism of claim 2, wherein the arresting vane has first and second ends in sequence in an upward direction of leakage flow of the working fluid;
in the circumference of inner hub, a plurality of the second end of arresting blade is the form setting of gathering together, and is a plurality of the first end of arresting blade is radial setting.
4. The seal mechanism of claim 3, wherein the second ends of adjacent arresting vanes are equally spaced.
5. A sealing mechanism according to claim 3 or 4, wherein the first ends of adjacent arresting vanes are equally spaced.
6. The seal mechanism of claim 2, wherein the plurality of arresting blades are disposed on a common cross-section perpendicular to the axis of rotation of the inner hub.
7. The seal mechanism of claim 3, wherein said arresting blades are disposed at an angle relative to the axis of rotation of the inner hub.
8. A sealing mechanism as claimed in claim 3 or claim 7, wherein the direction of flow of working fluid from the gap between adjacent said arresting blades is opposite to the direction of rotation of the inner hub.
9. An axial flow compressor comprising a sealing mechanism according to any one of claims 1 to 8.
10. A gas turbine engine comprising an axial compressor according to claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010803791.7A CN111878450A (en) | 2020-08-11 | 2020-08-11 | Sealing mechanism, axial flow compressor and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010803791.7A CN111878450A (en) | 2020-08-11 | 2020-08-11 | Sealing mechanism, axial flow compressor and gas turbine |
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| Publication Number | Publication Date |
|---|---|
| CN111878450A true CN111878450A (en) | 2020-11-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010803791.7A Pending CN111878450A (en) | 2020-08-11 | 2020-08-11 | Sealing mechanism, axial flow compressor and gas turbine |
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| CN (1) | CN111878450A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112627907A (en) * | 2020-12-21 | 2021-04-09 | 中国航发沈阳发动机研究所 | Method for improving sealing characteristic of labyrinth sealing structure and labyrinth sealing structure |
-
2020
- 2020-08-11 CN CN202010803791.7A patent/CN111878450A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112627907A (en) * | 2020-12-21 | 2021-04-09 | 中国航发沈阳发动机研究所 | Method for improving sealing characteristic of labyrinth sealing structure and labyrinth sealing structure |
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