CN111550292A - Intermediate pressure cylinder vortex cooling optimization method and cooling structure thereof - Google Patents
Intermediate pressure cylinder vortex cooling optimization method and cooling structure thereof Download PDFInfo
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- CN111550292A CN111550292A CN202010334038.8A CN202010334038A CN111550292A CN 111550292 A CN111550292 A CN 111550292A CN 202010334038 A CN202010334038 A CN 202010334038A CN 111550292 A CN111550292 A CN 111550292A
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- pressure cylinder
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
- F05D2260/2212—Improvement of heat transfer by creating turbulence
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A rectifier corresponding to a jet flow orifice is arranged at the upstream of the outlet of each jet flow pipe arranged on the wall surface of a cavity of a medium pressure cylinder along the jet flow direction, the outlet direction of the jet flow is corrected through the rectifier, the upstream cross flow is disturbed, the flow velocity of the cross flow and the upstream diffusion of the steam flow are reduced, the circumferential speed of the steam flow is closer to the tangential velocity of the surface of a medium pressure rotor, the penetrating power of the jet flow is enhanced, and therefore the cooling effect of the surface of the rotor is effectively improved. The jet flow outlet direction can be corrected, the upstream diffusion of the steam flow is reduced, and the circumferential speed of the steam flow is closer to the tangential speed of the surface of the medium-pressure rotor, so that the surface temperature of the medium-pressure rotor is effectively reduced, and the cooling effect is improved; meanwhile, the triangular wing rectifier can disturb the upstream transverse flow, reduce the flow velocity of the transverse flow, enhance the penetrating power of jet flow and play a role in improving the cooling effect; in addition, the invention has simple structure, convenient processing, lower cost and good engineering application value.
Description
Technical Field
The invention relates to the technology in the field of steam turbines, in particular to an optimization method for vortex cooling of a medium pressure cylinder and a cooling structure thereof.
Background
The medium-pressure rotor is used as a key component of thermal power generation, has a large diameter and is in direct contact with high-temperature reheated steam, the endurance strength of the medium-pressure rotor can be rapidly reduced along with the continuous improvement of steam inlet parameters, the creep rate can also be rapidly increased, and effective cooling measures need to be taken. The medium pressure cylinder vortex cooling technology is a technology without introducing external cooling gas, high-temperature reheat steam is directly adopted, a vortex is formed in a medium pressure cavity by entering a tangential jet pipe at a certain speed, the surface of a medium pressure rotor is cooled, the temperature sensed by the surface of the rotor is the total temperature of near-wall steam flow relative to the surface of the rotor, the prerotation theory in a turbine disc cavity is consulted, when the jet speed is constant, the circumferential speed difference of the jet flow and the tangential speed difference of the surface of the rotor are smaller, the temperature of the wall surface of the rotor is lower, and the cooling effect is better. However, in the case of the medium-pressure vortex cooling technology, further improvements are found, such as the high jet velocity, the high upstream diffusion of the steam flow, and thus the poor cooling of the rotor surface; secondly, the cross flow velocity inside the medium-pressure cavity is also high, reducing the penetration capacity of the jet and also deteriorating the cooling effect.
For the medium pressure cylinder vortex cooling technology, in order to fully exert the cooling function, the key is to reduce the upstream diffusion of the steam flow and make the tangential velocity of the steam flow as close as possible to the tangential velocity of the surface of the medium pressure rotor. The steam flow direction at the outlet of the jet pipe is reasonably corrected, and the surface of the medium-pressure rotor can be sufficiently cooled, so that the service life of the medium-pressure rotor is prolonged, the running safety of the whole unit is enhanced, and the unit efficiency is improved.
Disclosure of Invention
Aiming at the defect that the steam flow at the outlet of a jet pipe diffuses upstream in the conventional medium-pressure cylinder vortex cooling technology, the invention provides a medium-pressure cylinder vortex cooling optimization method and a cooling structure thereof, which can correct the direction of the jet outlet, reduce the upstream diffusion of the steam flow, and enable the circumferential speed of the steam flow to be closer to the tangential speed of the surface of a medium-pressure rotor, thereby effectively reducing the surface temperature of the medium-pressure rotor and improving the cooling effect; meanwhile, the triangular wing rectifier can disturb the upstream transverse flow, reduce the flow velocity of the transverse flow, enhance the penetrating power of jet flow and play a role in improving the cooling effect; in addition, the invention has simple structure, convenient processing, lower cost and good engineering application value.
The invention is realized by the following technical scheme:
the invention relates to an optimization method for vortex cooling of a medium pressure cylinder, wherein a rectifier corresponding to a jet orifice is arranged at the upstream of the outlet of each jet pipe arranged on the wall surface of a cavity of the medium pressure cylinder along the jet direction, the outlet direction of the jet is corrected through the rectifier, the upstream cross flow is disturbed, the flow velocity of the cross flow and the upstream diffusion of the steam flow are reduced, the circumferential speed of the steam flow is closer to the tangential velocity of the surface of a medium pressure rotor, the penetrating power of the jet is enhanced, and the cooling effect of the surface of the rotor is effectively improved.
The rectifier is a pentahedron symmetrical structure of a triangular wing type, the middle section of the rectifier is an arc obtuse triangle, the front end of the rectifier is provided with a protruding part along the jet flow direction (the rotation direction of the rotor).
The symmetrical structure is as follows: the rectifier is of a symmetrical structure along the span direction, and the symmetrical center plane is superposed with the axis of the jet pipe.
The obtuse-angle-like triangle is as follows: the included angle beta between the edge of the rectifier on the middle section along the jet flow direction and the arc edge on the wall surface of the chamber is 140-170 degrees; the length of a side H along the jet direction on the middle section is 0.1H to 0.4H, wherein: h is the chamber height; the distance l from the starting point to the end point along the inner wall surface of the chamber on the middle section is 1.0D-2.0D, the fillet radius r1 at the convex part on the middle section is 0.1D-0.4D, the fillet radius r2 at the connecting part of the obtuse angle opposite side and the inner wall surface of the chamber on the middle section is 2D-4D, and the span width b is 1.5D-2.5D, wherein: d is the inner diameter of the jet pipe.
The position upstream along the jet flow direction specifically refers to: the smooth transition is formed between the upper edge of the convex curved surface of the convex part of the rectifier and the orifice of the jet pipe on the wall surface of the chamber, and the smooth transition is formed between the curved surface at the tail end of the rectifier and the end part of the wall surface of the chamber.
The number of the jet pipes is more than 1 and the jet pipes are uniformly distributed along the circumferential direction.
The included angle between the axial line of the jet pipe and the tangential direction of the wall surface of the chamber is 10-30 degrees.
Technical effects
The invention integrally solves the technical problems that in the medium-pressure vortex cooling technology, tangential jet flow is seriously diffused upstream, the cooling effect cannot be fully exerted, the cross flow velocity inside a medium-pressure cavity is high, the penetration capacity of the jet flow is reduced, and the cooling capacity is deteriorated.
Compared with the prior art, the invention corrects the direction of the jet flow and disturbs the upstream transverse flow through the triangular wing rectifier, reduces the diffusion effect of the upstream steam flow, ensures that the circumferential speed of the steam flow is closer to the tangential speed of the surface of the medium-pressure rotor, obviously enhances the cooling effect, reduces the flow speed of the transverse flow, enhances the penetrating power of the jet flow and obviously improves the cooling effect.
Drawings
FIG. 1 is a general schematic view of the invention in vortex cooling of an intermediate pressure cylinder;
FIG. 2 is a schematic mid-section view of a delta airfoil rectifier;
FIG. 3 is a perspective view of a delta wing rectifier;
FIG. 4 is a schematic meridional cross-sectional view of a delta airfoil rectifier;
FIG. 5 is an overall perspective view of an optimized structure for medium-pressure vortex cooling;
FIG. 6 is a schematic view of the direction of the vapor flow in the present invention;
in the figure: 1 jet pipe, 2 delta wing rectifier, 3 medium pressure rotor, 4 chamber wall.
Detailed Description
As shown in fig. 1 to 6, the present embodiment relates to a cooling structure for improving the vortex cooling effect of an intermediate pressure cylinder, and specifically includes: the rectifier is positioned at the upstream of each jet pipe outlet along the jet flow direction and corresponds to the jet flow hole, the triangular wing type is of a triangular wing type symmetrical structure, the front end curved surface and the tail end curved surface are respectively in smooth transition with the jet flow pipe hole of the wall surface of the chamber and the end part of the wall surface of the chamber, and one side of the bulge is along the jet flow direction.
In this embodiment, the efflux pipe figure of arranging on the cavity wall is greater than 1, and along circumference evenly distributed, and the contained angle alpha between efflux pipe axis and the cavity internal wall tangential direction 10 ~ 30, and the efflux pipe is the pipe, also can take other shapes, and when taking other shapes, D is the span length in efflux drill way. For the cooling structure in this embodiment, the jet pipe holes are preferably circular.
As shown in fig. 4, the method for optimizing the vortex cooling of the intermediate pressure cylinder specifically includes: after the steam flow is jetted into the cavity from the orifice through the jet pipe, the triangular wing rectifier at the upstream of the orifice has a limiting effect on the flow direction, so that the upstream diffusion of the steam flow is reduced, the circumferential speed of the steam flow is closer to the tangential speed of the surface of the rotor, the total temperature of the steam flow relative to the surface of the rotor is smaller, the cooling effect of the medium-pressure rotor is effectively improved, the service life of the medium-pressure rotor is prolonged, and the operation safety of the whole steam turbine set is improved. In addition, the triangular wing rectifier has a certain disturbance effect on the upstream transverse flow, the flow velocity of the transverse flow can be reduced, the penetrating power of jet flow is enhanced, and the cooling effect is also improved. A specific example will be given below to further explain the present embodiment.
Specifically, in this embodiment, the number of jet pipes is 4, and the jet pipes are arranged periodically along the circumference at equal intervals, and the jet pipe holes are circular holes, the diameter D is 30mm, the included angle α between the axis of the jet pipe and the tangential direction of the inner wall surface of the chamber is 20 °, and the height H of the chamber is 40 mm. Correspondingly, in the rectifier in the present embodiment, the side length H of the triangular airfoil rectifier on the cross section along the jet flow direction is 0.3H-12 mm, the obtuse angle β between the side along the jet flow direction and the arc-shaped side on the chamber wall surface is 160 °, the distance l from the starting point to the end point along the inner wall surface of the chamber is 1.5D-45 mm, the fillet radius r1 of the protrusion is 0.2D-6 mm, and the fillet radius r2 of the connection point of the opposite side of the obtuse angle and the inner wall surface of the chamber is 2.5D-75 mm. The spanwise width of the triangular airfoil rectifier is 2D (60 mm), the fillet radius r3 on two sides of the triangular airfoil rectifier on a meridian section is 0.1D (2.5 mm), the surface of the whole triangular airfoil rectifier is smooth and has no edge angle, and the transition between the surface of the whole triangular airfoil rectifier and a jet flow orifice and an end wall is smooth.
When the steam flows into the chamber through the jet pipe 1 on the wall surface 4 of the chamber, the triangular wing rectifier 2 corrects the flow direction of the jet flow at the orifice, reduces the upstream diffusion of the steam flow, and makes the circumferential speed of the steam flow closer to the tangential speed of the surface of the rotor, thereby effectively reducing the surface temperature of the medium-pressure rotor and obviously improving the cooling effect of the rotor. In addition, the triangular wing rectifier has a disturbing effect on transverse flow, so that the flow velocity of the transverse flow is reduced, the penetrating power of jet flow is enhanced, the cooling effect of the rotor is improved, the running safety of a unit can be effectively improved, and the service life of the medium-pressure rotor is prolonged.
The foregoing embodiments may be modified in many different ways by those skilled in the art without departing from the spirit and scope of the invention, which is defined by the appended claims and all changes that come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.
Claims (7)
1. A method for optimizing eddy current cooling of a medium pressure cylinder is characterized in that a rectifier corresponding to an orifice of a jet flow is arranged at the upstream of the outlet of each jet flow pipe arranged on the wall surface of a cavity of the medium pressure cylinder along the jet flow direction, the outlet direction of the jet flow is corrected through the rectifier, the upstream cross flow is disturbed, the flow velocity of the cross flow and the upstream diffusion of the steam flow are reduced, the circumferential speed of the steam flow is closer to the tangential velocity of the surface of a medium pressure rotor, the penetrating power of the jet flow is enhanced, and therefore the cooling effect of the surface of the rotor is effectively improved;
the rectifier is a pentahedron symmetrical structure of a triangular wing type, the middle section of the rectifier is an arc obtuse triangle, the front end of the rectifier is provided with a protruding portion along the jet flow direction, and the front end of the rectifier is provided with a triangular wing type.
2. The method for optimizing vortex cooling of a medium pressure cylinder according to claim 1, wherein said symmetrical structure is: the rectifier is of a symmetrical structure along the span direction, and the symmetrical center plane is superposed with the axis of the jet pipe.
3. The method for optimizing vortex cooling of a medium pressure cylinder according to claim 1, wherein said obtuse triangle is: the included angle beta between the edge of the rectifier on the middle section along the jet flow direction and the arc edge on the wall surface of the chamber is 140-170 degrees; the length of a side H along the jet direction on the middle section is 0.1H to 0.4H, wherein: h is the chamber height; the distance l from the starting point to the end point along the inner wall surface of the chamber on the middle section is 1.0D-2.0D, the fillet radius r1 at the convex part on the middle section is 0.1D-0.4D, the fillet radius r2 at the connecting part of the obtuse angle opposite side and the inner wall surface of the chamber on the middle section is 2D-4D, and the span width b is 1.5D-2.5D, wherein: d is the diameter of the jet pipe.
4. The method for optimizing vortex cooling of a medium pressure cylinder according to claim 1, wherein the upstream in the jet flow direction specifically means: the smooth transition is formed between the upper edge of the convex curved surface of the convex part of the rectifier and the orifice of the jet pipe on the wall surface of the chamber, and the smooth transition is formed between the curved surface at the tail end of the rectifier and the end part of the wall surface of the chamber.
5. The method for optimizing vortex cooling of a medium pressure cylinder according to claim 1, wherein the number of the jet pipes is more than 1 and is uniformly distributed along the circumferential direction.
6. The vortex cooling optimization method for the intermediate pressure cylinder as claimed in claim 1, wherein an included angle between the axis of the jet pipe and the tangential direction of the wall surface of the chamber is 10 ° to 30 °.
7. A rectifier for implementing the optimization method of any one of claims 1 to 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202010334038.8A CN111550292A (en) | 2020-04-24 | 2020-04-24 | Intermediate pressure cylinder vortex cooling optimization method and cooling structure thereof |
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| CN202010334038.8A CN111550292A (en) | 2020-04-24 | 2020-04-24 | Intermediate pressure cylinder vortex cooling optimization method and cooling structure thereof |
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| CN202010334038.8A Pending CN111550292A (en) | 2020-04-24 | 2020-04-24 | Intermediate pressure cylinder vortex cooling optimization method and cooling structure thereof |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113250754A (en) * | 2021-04-22 | 2021-08-13 | 中国民用航空飞行学院 | Flow structure for counter-rotating disc cavity |
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Cited By (2)
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| CN113250754B (en) * | 2021-04-22 | 2023-05-05 | 中国民用航空飞行学院 | Flow structure for turntable cavity |
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Application publication date: 20200818 |