CN115949475A - High-temperature turbine disc cavity sealing structure based on multi-wing centrifugal blades and turbine - Google Patents
High-temperature turbine disc cavity sealing structure based on multi-wing centrifugal blades and turbine Download PDFInfo
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- CN115949475A CN115949475A CN202211654058.9A CN202211654058A CN115949475A CN 115949475 A CN115949475 A CN 115949475A CN 202211654058 A CN202211654058 A CN 202211654058A CN 115949475 A CN115949475 A CN 115949475A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/40—Solar thermal energy, e.g. solar towers
- Y02E10/46—Conversion of thermal power into mechanical power, e.g. Rankine, Stirling or solar thermal engines
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Abstract
The invention relates to the technical field of turbines, and provides a high-temperature turbine disc cavity sealing structure based on multi-wing centrifugal blades and a turbine, wherein the sealing structure at least comprises: the rear wall surface of the turbine guide vane disc; a sealing flow channel suitable for sealing gas flow is formed in a space between the front wall surface of the turbine moving impeller disc and the rear wall surface of the turbine guide vane disc; the multi-wing centrifugal blade is arranged along the circumferential direction of the front wall surface of the turbine moving impeller disc at intervals. This structure of obturating, when the impeller wheel dish of turbine is high-speed rotatory, utilize many wings centrifugal blade to promote the gaseous motion to turbine disc chamber outer fringe direction along the runner of obturating of the obturating of turbine disc intracavity to restriction high temperature gas passes through the runner of obturating invades to the turbine disc intracavity, under the gaseous prerequisite of not increasing the obturating, improves the effect of obturating through the gaseous velocity of flow that increases the obturating, avoids entering turbine mainstream runner and mainstream mixing because of the air conditioning of obturating is excessive and influences the turbine aerodynamic performance.
Description
Technical Field
The invention relates to the technical field of turbines, in particular to a high-temperature turbine disc cavity sealing structure based on multi-wing centrifugal blades and a turbine.
Background
In recent years, turbines utilizing pressure energy and heat energy of gas working media are widely applied, have various structural forms and provide electric power and power for industrial production and people's life. According to carnot's law, in order to have a higher energy conversion rate per unit volume of a turbo device, it is necessary to increase the intake air temperature of the turbo. However, in the actual operation process, because the pressure of the high-temperature gas in the main flow passage is high, a part of the high-temperature gas can intrude into the turbine disc cavity under the action of pressure difference and form ablation on the impeller disc rotating at high speed, and the operation safety is seriously influenced, so that the control of intrusion of the high-temperature gas working medium into the turbine disc cavity by adopting a proper technical means is an important way for improving the operation safety of the turbine.
At present, a plurality of technical methods for controlling gas to invade a disc cavity comprise various rim sealing structures, cooling gas jet flow and the like, and the basic principle of the method is as follows: the safety problem caused by overheating of the turbine disk is prevented by increasing the flow resistance of the high-temperature gas invading into the disk cavity and suppressing the gas invasion in combination with the ejection of cold gas from the disk cavity to the turbine main channel. However, in the prior art, when the gas is controlled to invade into the disc cavity, the sealing cold gas passes through the complex wheel rim sealing gap to cause insufficient sealing capability, and the disc structure of the high-temperature gas contact wheel is constructed to be an overheating problem.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is that the proposal number HA202208747 for controlling the gas invasion into the disc cavity in the prior art
When the sealing cold air passes through the complex rim sealing gap, the sealing capacity is insufficient, and the high-temperature gas contact wheel disc structure is constructed to be an overheating problem, so that the high-temperature turbine disc cavity sealing structure based on the multi-wing centrifugal blades and the turbine are provided.
In order to solve the technical problems, the technical scheme of the invention is as follows:
a high temperature turbine disk cavity sealing structure based on multi-wing centrifugal blades at least comprises: the rear wall surface of the turbine guide vane disc; a sealing flow channel suitable for sealing gas flow is formed in a space between the front wall surface of the turbine moving impeller disc and the rear wall surface of the turbine guide vane disc; the multi-wing centrifugal blades are arranged along the circumferential direction of the front wall surface of the turbine moving impeller disc at intervals and are suitable for pushing sealing gas in a turbine disc cavity to move towards the outer edge direction of the turbine disc cavity along the sealing flow channel when the impeller disc of the turbine rotates at a high speed so as to limit high-temperature gas from invading into the turbine disc cavity through the sealing flow channel.
Further, the middle arc form of the multi-wing centrifugal blade comprises one or more of a single arc form, a segmented arc form and a cubic B-shaped strip form.
Further, the cross-sectional shape of the multi-winged centrifugal blade includes a NACA airfoil and/or a Clark airfoil.
Further, the sealing flow channel gradually shrinks along the flowing direction of the sealing gas.
Furthermore, the through-flow cross section of the sealed flow channel has one or more of a linear type contracted cross section, a circular arc-shaped contracted cross section and a spline curve type contracted cross section.
Furthermore, the inlet radius of the cross section of the sealing flow channel is consistent with the inlet radius of the multi-wing centrifugal blade; the radius of the section outlet of the sealing flow channel is consistent with that of the outlet of the multi-wing centrifugal blade; the section shape of the sealing flow channel is consistent with the blade height change of the multi-wing centrifugal blade.
A turbine comprises the high-temperature turbine disc cavity sealing structure based on the multi-wing centrifugal blades.
Further, the types of turbines include axial, mixed flow, single stage configurations, and multi-stage junction model number HA202208747
One or more of the following.
Further, the high-temperature working medium source of the turbine comprises one or more of atmospheric environment, engine tail gas, fuel gas, industrial exhaust flue gas, compressed air, solar heat collector high-temperature gas, heat accumulator high-temperature gas and chemical process high-temperature gas.
The technical scheme of the invention has the following advantages:
according to the high-temperature turbine disc cavity sealing structure based on the multi-wing centrifugal blades, the multi-wing centrifugal blades are arranged on the front wall surface of the turbine moving blade wheel disc, when the impeller wheel disc of a turbine rotates at a high speed, sealing gas in the turbine disc cavity is pushed to move towards the outer edge direction of the turbine disc cavity along the sealing flow channel by the multi-wing centrifugal blades, so that high-temperature gas is limited from invading into the turbine disc cavity through the sealing flow channel, and the problem that the high-temperature gas is contacted with the wheel disc junction to form overheating is avoided; and on the premise of not increasing the sealing gas, the sealing effect is improved by increasing the flow velocity of the sealing gas, and the influence on the pneumatic performance of the turbine caused by the mixing of the sealing cold gas entering the main flow channel of the turbine and the main flow due to the excessive sealing cold gas is avoided.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic diagram of a high-temperature turbine disk cavity sealing structure based on a multi-wing centrifugal blade in an embodiment of the invention;
FIG. 2 is a schematic view at the multi-winged centrifugal blade of FIG. 1;
FIG. 3 is a schematic view of the sealed flow channel of FIG. 1;
FIG. 4 is an enlarged view of portion A of the embodiment of FIG. 3;
FIG. 5 is an enlarged view of a portion A of the embodiment of FIG. 3;
i scheme number HA202208747
Fig. 6 is an enlarged view of a portion a of the embodiment of fig. 3.
Reference numerals:
1. moving blades; 2. a moving impeller hub; 3. a multi-winged centrifugal blade; 4. the rear wall surface of the turbine guide vane disc; 5. the front wall surface of the turbine moving impeller disc; 6. sealing the flow channel; 7. an impeller rotating shaft; 8. a guide vane; 9. sealing the gas; 10. high temperature gas working medium.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in a specific case to those of ordinary skill in the art.
Furthermore, the technical features involved in the different embodiments of the invention described below are as long as the other version number HA202208747
They can be combined without conflict.
FIG. 1 is a schematic diagram of an exemplary embodiment of the present invention based on multiple airfoilsA schematic diagram of a high-temperature turbine disk cavity sealing structure of the core blade; FIG. 2 is a schematic view at the multi-airfoil centrifugal blade of FIG. 1; FIG. 3 is a schematic view of the sealed flow channel of FIG. 1; as shown in fig. 1, fig. 2 and fig. 3, in the present embodiment, a high temperature turbine disk cavity sealing structure based on a multi-wing centrifugal blade 3 is provided, which at least includes: a turbine vane disk rear wall surface 4; a sealing flow passage 6 suitable for sealing gas 9 to flow is formed in a space between the front wall surface 5 of the turbine moving impeller disc and the rear wall surface 4 of the turbine guide impeller disc; the multi-wing centrifugal blades 3 are arranged at intervals along the circumferential direction of the front wall surface 5 of the turbine moving impeller disc, and the multi-wing centrifugal blades 3 are suitable for pushing sealing gas 9 in the cavity of the turbine disc to move towards the outer edge direction of the cavity of the turbine disc along the sealing flow channel 6 when the impeller disc of the turbine rotates at a high speed so as to limit the invasion of high-temperature gas into the cavity of the turbine disc through the sealing flow channel 6. Wherein, the number of the multi-wing centrifugal blades 3 and the inlet radius R of the multi-wing centrifugal blades 3 1 With the outlet radius R of the multi-wing centrifugal blade 3 2 The inlet and outlet airflow angle and the arc length of the blade can be determined according to the actual geometric dimension and the operation condition.
According to the high-temperature turbine disc cavity sealing structure based on the multi-wing centrifugal blades 3, the multi-wing centrifugal blades 3 are arranged on the front wall surface 5 of the turbine moving impeller disc, when the impeller disc of the turbine rotates at a high speed, the multi-wing centrifugal blades 3 are used for pushing sealing gas 9 in the turbine disc cavity to move towards the outer edge direction of the turbine disc cavity along the sealing flow channel 6, so that high-temperature gas is limited from invading into the turbine disc cavity through the sealing flow channel 6, and the problem that the high-temperature gas is contacted with the wheel disc structure to cause overheating is avoided; moreover, on the premise of not increasing the sealing gas 9, the sealing effect is improved by increasing the flow velocity of the sealing gas 9, and the influence on the pneumatic performance of the turbine caused by the mixing of the sealing cold gas entering a main flow channel of the turbine and the main flow due to the excessive amount of the sealing cold gas is avoided.
The middle arc form of the multi-wing centrifugal blade 3 comprises one or more of a single arc form, a segmented arc form and a cubic B-shaped strip form.
Wherein the cross-sectional shape of the multi-winged centrifugal blade 3 comprises a NACA airfoil and/or a Clark airfoil.
Wherein the sealing flow channel 6 gradually shrinks in the flow direction of the sealing gas 9. So arranged, I's scheme number HA202208747
Through the blast effect of the multi-wing centrifugal blades 3, the low-temperature sealing gas 9 can be promoted to enter a main stream, the high-temperature main stream gas is prevented from entering a disk cavity space, the temperature of the rear wall surface 4 of the turbine guide vane disk and the front wall surface 5 of the turbine movable vane disk is reduced, the wall surfaces are prevented from being burnt out, and the purpose of protecting the turbine structure is achieved.
FIG. 4 is an enlarged view of section A of the embodiment of FIG. 3; FIG. 5 is an enlarged view of portion A of the alternate embodiment of FIG. 3; FIG. 6 is an enlarged view of portion A of the alternate embodiment of FIG. 3; as shown in fig. 4, 5 and 6, the flow cross-sectional shape of the sealed flow channel 6 includes one or more of a straight-line constricted cross-section (fig. 4), a circular-arc constricted cross-section (fig. 5) and a spline-curve constricted cross-section (fig. 6). So set up, can further accelerate the cooling gas of obturating, hinder the invasion of high temperature mainstream to the rim plate cavity.
Wherein, the section inlet radius of the sealing runner 6 is consistent with the inlet radius of the multi-wing centrifugal blade 3; the radius of the section outlet of the sealing flow channel 6 is consistent with that of the outlet of the multi-wing centrifugal blade 3; the cross section shape of the sealing flow channel 6 is consistent with the blade height change of the multi-wing centrifugal blade 3.
In another embodiment, a turbine is provided, which comprises the high-temperature turbine disk cavity sealing structure based on the multi-wing centrifugal blades 3. Wherein, the turbine also comprises a moving blade 1, a moving blade hub 2, an impeller rotating shaft 7 and a guide vane 8; the moving blades 1 are arranged on a moving blade hub 2, the guide blades 8 are mounted on a turbine guide blade disc, and the moving blade hub 2 and an impeller disc connected with the moving blade hub can rotate around an impeller rotating shaft 7. When the high-temperature gas working medium 10 works, the high-temperature gas working medium firstly enters the guide vane, is accelerated in the guide vane 8 and then enters the impeller, and pushes the impeller wheel disc to rotate to do work when flowing through the moving blade 1. The high-temperature gas working medium 10 of the turbine is from atmospheric environment, engine tail gas, fuel gas, industrial exhaust flue gas, compressed air, high-temperature gas of a solar heat collector, high-temperature gas of a heat accumulator, high-temperature gas of a chemical process and the like.
The turbine is of a type including one or more of an axial flow type, a mixed flow type, a single stage structure and a multi-stage structure. The number, the geometric shape, the structural size and the rotating speed of the turbines can be determined according to overall thermodynamic design parameters. In summary, the present application relates to a high temperature turbine disk based on multi-wing centrifugal blades, i.e. the design No. HA202208747
The cavity structure and the turbine of obturating, under the unchangeable condition of gas volume guaranteeing to obturate, based on the principle that multi-wing centrifugal fan impeller rotates and increases gaseous kinetic energy, can effectively restrain the invasion of high temperature gas, guarantee high temperature turbine operation security and life.
The high temperature turbine disc cavity sealing structure based on the multi-wing centrifugal blades and the turbine in the application have the advantages that the section shape of the sealing flow channel can be optimally designed according to the actual operation working conditions and the conditions of the high temperature turbine, and therefore the high temperature turbine disc cavity sealing structure can be suitable for the high temperature turbine operating under different working conditions.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.
Claims (9)
1. The utility model provides a high temperature turbine dish chamber structure of obturating based on multi-wing centrifugal blade which characterized in that includes at least:
the rear wall surface of the turbine guide vane disc;
a sealing flow channel suitable for sealing gas flow is formed in a space between the front wall surface of the turbine moving impeller disc and the rear wall surface of the turbine guide vane disc;
the multi-wing centrifugal blades are arranged along the circumferential direction of the front wall surface of the turbine moving impeller disc at intervals and are suitable for pushing sealing gas in a turbine disc cavity to move towards the outer edge direction of the turbine disc cavity along the sealing flow channel when the impeller disc of the turbine rotates at a high speed so as to limit high-temperature gas from invading into the turbine disc cavity through the sealing flow channel.
2. The high-temperature turbine disk cavity sealing structure based on the multi-wing centrifugal blade according to claim 1,
the middle arc form of the multi-wing centrifugal blade comprises one or more of a single arc form, a segmented arc form and a cubic B-shaped strip form.
3. The high-temperature turbine disk cavity sealing structure based on the multi-wing centrifugal blade according to claim 1,
the cross-sectional shape of the multi-winged centrifugal blade comprises a NACA airfoil and/or a Clark airfoil.
4. The high-temperature turbine disk cavity sealing structure based on the multi-wing centrifugal blade according to claim 1,
the sealing flow channel gradually shrinks along the flowing direction of the sealing gas.
5. The high-temperature turbine disk cavity sealing structure based on the multi-wing centrifugal blade according to claim 4,
the through-flow section of the sealed flow channel has one or more of a linear type contraction section, a circular arc type contraction section and a spline curve type contraction section.
6. The high-temperature turbine disk cavity sealing structure based on the multi-wing centrifugal blade according to claim 4,
the inlet radius of the cross section of the sealing flow channel is consistent with the inlet radius of the multi-wing centrifugal blade;
the radius of the section outlet of the sealing flow channel is consistent with that of the outlet of the multi-wing centrifugal blade;
the cross section shape of the sealing flow channel is consistent with the blade height change of the multi-wing centrifugal blade.
7. A turbine comprising a multi-airfoil centrifugal blade based high temperature turbine disk cavity seal structure of any of claims 1-6.
8. The turbine of claim 7, wherein the type of turbine comprises one or more of an axial flow, a mixed flow, a single stage configuration, and a multi-stage configuration.
9. The turbine of claim 7, wherein the high temperature working medium source of the turbine comprises one or more of atmospheric environment, engine exhaust, gas, industrial exhaust flue gas, compressed air, solar collector high temperature gas, regenerator high temperature gas, and chemical process high temperature gas.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211654058.9A CN115949475A (en) | 2022-12-20 | 2022-12-20 | High-temperature turbine disc cavity sealing structure based on multi-wing centrifugal blades and turbine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211654058.9A CN115949475A (en) | 2022-12-20 | 2022-12-20 | High-temperature turbine disc cavity sealing structure based on multi-wing centrifugal blades and turbine |
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| CN115949475A true CN115949475A (en) | 2023-04-11 |
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| CN202211654058.9A Pending CN115949475A (en) | 2022-12-20 | 2022-12-20 | High-temperature turbine disc cavity sealing structure based on multi-wing centrifugal blades and turbine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117928832A (en) * | 2024-03-21 | 2024-04-26 | 太仓点石航空动力有限公司 | Turbine disc cavity sealing efficiency testing method and system |
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- 2022-12-20 CN CN202211654058.9A patent/CN115949475A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117928832A (en) * | 2024-03-21 | 2024-04-26 | 太仓点石航空动力有限公司 | Turbine disc cavity sealing efficiency testing method and system |
| CN117928832B (en) * | 2024-03-21 | 2024-05-17 | 太仓点石航空动力有限公司 | Turbine disc cavity sealing efficiency testing method and system |
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