CN116522535A - Endwall design method and endwall design system for improving endwall slot jet cooling efficiency of turbine stator blade - Google Patents
Endwall design method and endwall design system for improving endwall slot jet cooling efficiency of turbine stator blade Download PDFInfo
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- CN116522535A CN116522535A CN202310487092.XA CN202310487092A CN116522535A CN 116522535 A CN116522535 A CN 116522535A CN 202310487092 A CN202310487092 A CN 202310487092A CN 116522535 A CN116522535 A CN 116522535A
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- 238000001816 cooling Methods 0.000 title claims abstract description 63
- 238000000034 method Methods 0.000 title claims abstract description 29
- 238000013461 design Methods 0.000 title claims abstract description 27
- 238000006073 displacement reaction Methods 0.000 claims description 9
- 230000008878 coupling Effects 0.000 claims description 4
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- 230000000694 effects Effects 0.000 description 11
- 238000002485 combustion reaction Methods 0.000 description 5
- 238000000465 moulding Methods 0.000 description 3
- 238000002679 ablation Methods 0.000 description 2
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- 230000009286 beneficial effect Effects 0.000 description 1
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- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
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Classifications
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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
- F01D25/08—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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F17/00—Digital computing or data processing equipment or methods, specially adapted for specific functions
- G06F17/10—Complex mathematical operations
- G06F17/18—Complex mathematical operations for evaluating statistical data, e.g. average values, frequency distributions, probability functions, regression analysis
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- G06F30/20—Design optimisation, verification or simulation
- G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
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- G06F7/00—Methods or arrangements for processing data by operating upon the order or content of the data handled
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- G06F7/544—Methods or arrangements for performing computations using exclusively denominational number representation, e.g. using binary, ternary, decimal representation using non-contact-making devices, e.g. tube, solid state device; using unspecified devices for evaluating functions by calculation
- G06F7/548—Trigonometric functions; Co-ordinate transformations
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/08—Fluids
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
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Abstract
The invention discloses an endwall design method and an endwall design system for improving the endwall slot jet cooling efficiency of a turbine stationary blade endwall. The local non-axisymmetric end wall modeling forms pits on the side of the blade end region near the pressure surface, and forms bulges on the side near the suction surface, so that the development of branches of the pressure side of the horseshoe vortex in the end region is changed, the influence of the branches on the slot jet is weakened, the cooling efficiency of the slot jet is increased, the temperature of the end wall is reduced, and the service life of the slot jet is prolonged. In addition, the partial shaping of smaller amplitude has little impact on aerodynamic losses of the turbine.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to an endwall design method for improving the endwall slot jet cooling efficiency of a turbine stationary blade endwall.
Background
The turbine is one of the high temperature components of the gas turbine power plant, in order to increase the power of the gas turbine, the inlet temperature of the turbine is gradually increased, and meanwhile, the temperature distribution of the outlet of the combustion chamber tends to be flattened due to the use of advanced combustion technologies such as lean oil premixing, dispersed combustion and the like, and the heat load of the end wall is obviously increased. Because of the installation clearance, gaps exist between the outlet of the combustion chamber and the inlet of the turbine stator blade, endwall slot jet flow is generally adopted to cool the endwall, and the endwall is derived from high-pressure low-temperature gas led out by the compressor and is a part of cooling of the high-temperature turbine end region.
In the end wall of a conventional stator blade, slot jet flow is limited by branches on the suction surface side and the pressure surface side of the horseshoe vortex, a wedge-shaped cold air coverage area is formed, and the cooling effect of the end wall near the pressure surface side is poor. When the gas turbine is continuously operated, an ablation phenomenon occurs on the end wall near the pressure surface side, and the safety and the service life of the gas turbine are seriously influenced.
In view of the above, it is desirable to design a tip wall design method for improving the cooling efficiency of the slot jet flow of the tip wall of the turbine stator blade, and improving the cooling effect of the near pressure surface side of the turbine tip wall.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides an end wall design method for improving the slot jet cooling efficiency of the end wall of a turbine stator blade, and the slot jet cooling efficiency and the cold air coverage area are further improved by changing a non-axisymmetric modeling method of the branching flow of the suction side and the pressure side of a horseshoe vortex.
The invention is realized by the following technical scheme:
an endwall design method for improving the cooling efficiency of slot jet flow of an endwall of a turbine stator blade comprises the following steps:
step 1, presetting a plurality of circumferential control curves along the axial direction within a preset range of a blade grid channel of a blade;
step 2, performing full-period sine function fitting on a plurality of circumferential control curves along the circumferential direction of the blade to obtain circumferential curves of a cooling modeling area to be constructed in the cascade channels;
step 3, controlling the maximum amplitude of a plurality of circumferential control curves along the axial direction of the blade by adopting a sine function to perform fitting, so as to obtain the radial control coefficient of each circumferential control curve;
and 4, fitting the circumferential curve of the cooling modeling area obtained in the step 2 and the radial control coefficient obtained in the step 3 to obtain a curved surface structure of the cooling modeling area in the cascade channel to be constructed.
Preferably, the cooling molding area of step 1 is located in the cascade channels within 40% of the axial chord length from the leading edge of the blade.
Preferably, the starting point and the ending point of the circumferential control curve are located on the pressure surface and the suction surface of the cascade channels, respectively.
Preferably, the circumferential curve of the cooling molding area in step 2 includes a concave circumferential curve of the pressure surface and a convex circumferential curve of the suction surface.
Preferably, the expression of the full-period sine function in step 2 is as follows:
wherein X represents the radial displacement of the end wall, i is the circumferential coordinate value of a certain point on the circumferential control line, a (z) is the circumferential coordinate value of the intersection point of the circumferential control line and the pressure surface of the blade, and b (z) is the circumferential coordinate value of the intersection point of the circumferential control line and the suction surface of the blade.
Preferably, the expression of the sine function in step 3 is as follows:
where k is the kth circumferential control curve and m is the total number of circumferential control curves.
Preferably, the curved surface structure of the cooling modeling area in the step 4 is positioned on the surface of the lower end wall of the blade and has a non-axisymmetric characteristic.
Preferably, the fitting method in step 4 is as follows:
H＝CA k X
wherein C is the maximum amplitude control coefficient, A k And X is the radial displacement of the end wall, and H is the radial displacement of the final end wall.
A system for endwall design methods to improve turbine vane endwall slot jet cooling efficiency includes,
the control curve module is used for presetting a plurality of circumferential control curves along the axial direction within a preset range of the blade grid channel of the blade;
the circumferential curve determining module is used for performing full-period sine function fitting on a plurality of circumferential control curves along the circumferential direction of the blade to obtain a circumferential curve of a cooling modeling area to be constructed in the blade grid channel;
the radial control coefficient determining module is used for controlling the maximum amplitude values of the plurality of circumferential control curves to fit by adopting a sine function along the axial direction of the blade to obtain the radial control coefficient of each circumferential control curve;
and the coupling module is used for fitting the circumferential curve and the radial control coefficient of the cooling modeling area to obtain the curved surface structure of the cooling modeling area in the cascade channel to be constructed.
Compared with the prior art, the invention has the following beneficial technical effects:
according to the end wall design method for improving the jet cooling efficiency of the slot of the end wall of the turbine stator blade, a circumferential curve of a cooling modeling area to be constructed and radial control coefficients of the circumferential control curves are obtained according to the set circumferential control curve and by combining a sine function; the two are fitted to obtain curved surface modeling of a cooling modeling area, and the cooling modeling area can control the flow of the horseshoe vortex suction surface branch and the pressure surface branch, so that the distribution of slot jet flow, namely cooling flow, in the circumferential direction of the end wall is increased, and the uneven temperature distribution of the end wall is improved, and the premature ablation of the gas turbine is avoided. The slot jet flow air film cooling effect between the combustion chamber and the stator blade of the gas turbine and the aeroengine can be improved.
Drawings
FIG. 1 is a circumferential control line distribution diagram of an end wall design method in an embodiment of the invention.
FIG. 2 is a circumferential modeling view of an end wall design method in an embodiment of the invention.
FIG. 3 is an axial modeling view of an end wall design method in an embodiment of the invention.
Fig. 4 is a cloud chart of conventional end wall air film cooling effect distribution in an embodiment of the invention.
Fig. 5 is a cloud chart of air film cooling effect distribution of a modeling end wall in an embodiment of the invention.
FIG. 6 is a graph of the average film cooling effect in the circumferential direction of the end wall in an embodiment of the invention.
Detailed Description
The invention will now be described in further detail with reference to the accompanying drawings, which illustrate but do not limit the invention.
An endwall design method for improving the cooling efficiency of slot jet flow of an endwall of a turbine stator blade comprises the following steps:
step 1, presetting a plurality of circumferential control curves along the axial direction within a preset range of blade grid channels of the blades.
As shown in fig. 1, the axial control curves are located in the cascade channels within 40% of the axial chord length from the leading edge of the blade, and the axial control curves are uniformly distributed along the axial direction, and the starting point and the ending point of the circumferential control curves are located on the pressure surface and the suction surface of the cascade channels respectively.
In this embodiment, 7 circumferential control curves are provided, but of course, more circumferential control curves, for example, 10 or 15 circumferential control curves may be provided.
And 2, performing full-period sine function fitting on a plurality of circumferential control curves along the circumferential direction from the pressure surface to the suction surface of the blade to obtain circumferential curves of the cooling modeling area to be constructed in the blade cascade channel.
The circumferential curve of the cooling molding zone includes a concave circumferential curve formed by the pressure surface and a convex circumferential curve formed by the suction surface, as shown in fig. 2.
The expression of the full-period sine function is as follows:
wherein X represents the radial displacement of the end wall, i is the circumferential coordinate value of a certain point on the circumferential control line, a (z) is the circumferential coordinate value of the intersection point of the circumferential control line and the pressure surface of the blade, and b (z) is the circumferential coordinate value of the intersection point of the circumferential control line and the suction surface of the blade.
And 3, controlling the maximum amplitude values of the plurality of circumferential control curves along the axial direction from the leading edge to the trailing edge of the blade by adopting a sine function to perform fitting, and obtaining the radial control coefficient of each circumferential control curve.
The expression of the sine function is as follows:
where k is the kth circumferential control curve and m is the total number of circumferential control curves.
In this embodiment, the radial control coefficients of each circumferential control curve are 0, 0.5, 0.866, 1, 0.866, 0.5, 0, respectively corresponding to 1 to 7 control curves, see fig. 3.
And 4, fitting the circumferential curve of the cooling modeling area obtained in the step 2 and the radial control coefficient obtained in the step 3 to obtain a curved surface structure of the cooling modeling area of the cascade channel to be constructed, wherein the curved surface structure of the cooling modeling area is positioned on the surface of the lower end wall of the blade and has non-axisymmetric characteristics.
The fitting formula is as follows:
H＝CA k X
wherein C is the maximum amplitude control coefficient, A k And X is the radial displacement of the endwall, H is the radial displacement of the final endwall, and the maximum value of H is +/-1% of the height of the turbine stator blade.
And 5, performing three-dimensional simulation on the structure of the cooling modeling area in the cascade channels.
Structural meshing is carried out on a non-axisymmetric end wall blade model with slot jet flow, three-dimensional simulation calculation is carried out, and the conclusion is as follows:
performing structural grid division and grid independence verification, wherein a turbulence model selects an SST k-w model; the inlet boundary condition is that the total temperature and the total pressure are uniformly distributed, the air inlet angle is 90 degrees, the outlet boundary is given with average static pressure, and the jet flow of the slot is kept constant.
The basic principle of the invention is to change the secondary flow distribution of the end region by three-dimensional concave-convex of the end wall, generate pits on the side near the pressure surface of the end wall and generate bulges on the side near the suction surface, so that the pressure surface branch of the horseshoe vortex is near the pressure surface, the entrainment effect of the horseshoe vortex on slot jet flow is weakened, the transverse diffusion of cold air on the end wall surface is enlarged, and the end wall is better protected. From the conventional end wall air film cooling effect distribution shown in fig. 4, the modeling end wall air film cooling effect distribution shown in fig. 5 and the circumferential average air film comparison before and after modeling of the end wall in fig. 6, it can be seen that the modeling method provided by the application can obviously increase the diffusion of slot jet flow on the end wall, and improve the protection effect of the cold air on the end wall.
In another embodiment, the invention also provides a system for improving the end wall design method of the turbine stator blade end wall slot jet cooling efficiency, which comprises a control curve module, a circumferential curve determining module, a radial control coefficient determining module and a coupling module.
The control curve module is used for presetting a plurality of circumferential control curves along the axial direction within a preset range of the blade grid channel of the blade;
the circumferential curve determining module is used for performing full-period sine function fitting on a plurality of circumferential control curves along the circumferential direction of the blade to obtain a circumferential curve of a cooling modeling area to be constructed in the blade grid channel;
the radial control coefficient determining module is used for controlling the maximum amplitude values of the plurality of circumferential control curves to fit by adopting a sine function along the axial direction of the blade to obtain the radial control coefficient of each circumferential control curve;
and the coupling module is used for fitting the circumferential curve and the radial control coefficient of the cooling modeling area to obtain the curved surface structure of the cooling modeling area in the cascade channel to be constructed.
The invention discloses an endwall design method for improving the endwall slot jet cooling efficiency of a turbine stationary blade endwall. The local non-axisymmetric end wall modeling forms pits on the side of the blade end region near the pressure surface, and forms bulges on the side near the suction surface, so that the development of branches of the pressure side of the horseshoe vortex in the end region is changed, the influence of the branches on the slot jet is weakened, the cooling efficiency of the slot jet is increased, the temperature of the end wall is reduced, and the service life of the slot jet is prolonged. In addition, the partial shaping of smaller amplitude has little impact on aerodynamic losses of the turbine. The method can determine the circumferential control curve as long as the axial modeling range and the maximum modeling amplitude are given. On a certain circumferential control curve, the radial amplitude of the axial control line is the maximum amplitude of the circumferential control line. The number of the circumferential control curves is 7, and the operation is simple and convenient.
The above is only for illustrating the technical idea of the present invention, and the protection scope of the present invention is not limited by this, and any modification made on the basis of the technical scheme according to the technical idea of the present invention falls within the protection scope of the claims of the present invention.
Claims (9)
1. The endwall design method for improving the cooling efficiency of the slot jet flow of the endwall of the turbine stator blade is characterized by comprising the following steps of:
step 1, presetting a plurality of circumferential control curves along the axial direction within a preset range of a blade grid channel of a blade;
step 2, performing full-period sine function fitting on a plurality of circumferential control curves along the circumferential direction of the blade to obtain circumferential curves of a cooling modeling area to be constructed in the cascade channels;
step 3, controlling the maximum amplitude of a plurality of circumferential control curves along the axial direction of the blade by adopting a sine function to perform fitting, so as to obtain the radial control coefficient of each circumferential control curve;
and 4, fitting the circumferential curve of the cooling modeling area obtained in the step 2 and the radial control coefficient obtained in the step 3 to obtain a curved surface structure of the cooling modeling area in the cascade channel to be constructed.
2. The endwall design method for improving turbine vane endwall slot jet cooling efficiency of claim 1, wherein said cooling modeling area of step 1 is located in a cascade channel within 40% axial chord length from a leading edge of the blade.
3. The endwall design method for improving turbine vane endwall slot jet cooling efficiency of claim 1, wherein a start point and an end point of the circumferential control curve are located on a pressure side and a suction side of the cascade channel, respectively.
4. The method of claim 1, wherein the circumferential profile of the cooling modeling area in step 2 includes a concave circumferential profile of the pressure surface and a convex circumferential profile of the suction surface.
5. The endwall design method for improving the cooling efficiency of a slot jet of a turbine stator vane endwall according to claim 1, wherein the expression of the full-period sine function in step 2 is as follows:
wherein X represents the radial displacement of the end wall, i is the circumferential coordinate value of a certain point on the circumferential control line, a (z) is the circumferential coordinate value of the intersection point of the circumferential control line and the pressure surface of the blade, and b (z) is the circumferential coordinate value of the intersection point of the circumferential control line and the suction surface of the blade.
6. The endwall design method for improving the cooling efficiency of a slot jet of a turbine vane endwall according to claim 1, wherein the expression of the sine function in step 3 is as follows:
where k is the kth circumferential control curve and m is the total number of circumferential control curves.
7. The endwall design method for improving the cooling efficiency of a slot jet flow of a turbine stator blade endwall according to claim 1, wherein the curved surface structure of the cooling modeling area in the step 4 is positioned on the lower endwall surface of the blade and has a non-axisymmetric characteristic.
8. The endwall design method for improving the cooling efficiency of a slot jet flow of a turbine stator blade endwall according to claim 1, wherein the fitting method in step 4 is as follows:
H＝CA k X
wherein C is the maximum amplitude control coefficient, A k And X is the radial displacement of the end wall, and H is the radial displacement of the final end wall.
9. A system of endwall design methods for improving turbine vane endwall slot jet cooling efficiency as claimed in any one of claims 1-8, comprising,
the control curve module is used for presetting a plurality of circumferential control curves along the axial direction within a preset range of the blade grid channel of the blade;
the circumferential curve determining module is used for performing full-period sine function fitting on a plurality of circumferential control curves along the circumferential direction of the blade to obtain a circumferential curve of a cooling modeling area to be constructed in the blade grid channel;
the radial control coefficient determining module is used for controlling the maximum amplitude values of the plurality of circumferential control curves to fit by adopting a sine function along the axial direction of the blade to obtain the radial control coefficient of each circumferential control curve;
and the coupling module is used for fitting the circumferential curve and the radial control coefficient of the cooling modeling area to obtain the curved surface structure of the cooling modeling area in the cascade channel to be constructed.
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| CN202310487092.XA CN116522535A (en) | 2023-04-28 | 2023-04-28 | Endwall design method and endwall design system for improving endwall slot jet cooling efficiency of turbine stator blade |
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| CN202310487092.XA CN116522535A (en) | 2023-04-28 | 2023-04-28 | Endwall design method and endwall design system for improving endwall slot jet cooling efficiency of turbine stator blade |
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