CN114439552B - Triangular pyramid-shaped flow guiding structure, turbine guider and gas turbine design method thereof - Google Patents
Triangular pyramid-shaped flow guiding structure, turbine guider and gas turbine design method thereof Download PDFInfo
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- CN114439552B CN114439552B CN202210090461.7A CN202210090461A CN114439552B CN 114439552 B CN114439552 B CN 114439552B CN 202210090461 A CN202210090461 A CN 202210090461A CN 114439552 B CN114439552 B CN 114439552B
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
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Abstract
The triangular pyramid-shaped flow guiding structure consists of 2 isosceles triangles and 2 right triangles, wherein the pointed ends face to the direction of the incoming flow of the sealed cold air, are positioned in the rotating disc cavity structure right in front of the front edge of the turbine guide vanes, are circumferentially arranged, and are consistent in number with the turbine guide vanes. The structure can be integrally milled with the turbine guide or separately processed into a metal ring belt with a triangular pyramid-shaped flow guiding structure, and then the metal ring belt is connected with the turbine guide by bolts. According to the turbine guide with the triangular pyramid-shaped flow guiding structure, the triangular pyramid-shaped flow guiding structure is arranged on the side wall surface of the guide in the cavity structure of the rotating disc at the upstream of the turbine guide, so that leakage flow is guided and disturbed, leakage flow loss caused by gas invasion is reduced, and the integral cooling efficiency of the end wall of the guide is improved. The triangular pyramid-shaped flow guide structure is arranged at the cavity structure of the rotating disc, has the characteristics of simple structure, no interference to main flow and good cooling effect, and can be used for various turbine guides.
Description
Technical Field
The invention belongs to the technical field of cooling of turbine blades of gas turbines, and discloses a turbine guide with a triangular pyramid-shaped guide structure.
Background
Gas turbine engines are a type of thermodynamic device based on the brayton cycle, which by virtue of its powerful output power and high thermal efficiency have been widely used in modern military and industrial applications.
The working environment of the gas turbine engine has the characteristics of high temperature, high pressure and high rotating speed, and experience shows that on the premise of unchanged engine size, the thrust of the gas turbine can be increased by 8-13% and the cycle efficiency can be improved by 2-4% when the turbine inlet temperature is increased by 56K. In order to achieve higher performance indexes, the temperature of the advanced gas turbine engine before the turbine can reach 1800-2100K, but the temperature resistance limit of turbine blade materials is far smaller than the inlet temperature of the turbine, wherein the existing temperature difference can be solved only by a complex blade cooling technology and a thermal insulation coating technology. At present, a mature blade cooling technology is an air film impact turbulent flow composite cooling technology, and a next generation cooling technology is a miniature cooling technology represented by double-layer walls. Compared with various cooling means of the blade body, the cooling means for the end wall of the turbine blade are relatively limited, and the problem of heat exchange deterioration at the end wall is also worth focusing on with the increase of the temperature before the turbine.
The cooling technology of the end wall area at the present stage is mainly an end wall air film cooling technology, and can be divided into upstream end wall air film cooling of the front edge of the blade, blade root end wall air film cooling of the pressure surface, downstream end wall air film cooling of the blade cascade channel and slit cooling of the blade cascade channel according to the positions. The flow heat exchange condition at the end wall of the turbine blade is very complex and has high heat convection intensity under the influence of the channel vortex and the horseshoe vortex, and leakage flow is required to be introduced to participate in cooling the end wall of the turbine blade in order to cope with the increasing temperature before the turbine.
Leakage flow refers to cold air used to cool the turbine disk and achieve a seal of the main stream gas and sink into the main stream at the rim. The flow structure and outflow characteristics of the leakage flow can be greatly affected by the main flow and the rotating disk cavity structure, with large circumferential non-uniformities.
The prior experimental study on the air film cooling of the end wall of the turbine guide mainly comprises the following steps: (1) the effect of purge flow (slit jet) on endwall film cooling efficiency was studied on a stationary cascade test bench (document 1) [ Xu Qingzong, du Jiang, wang Pei, etc.. Turbine end discrete step slit film cooling characteristics study [ J ]. Engineering thermophysics journal, 2021, 42 (9): 6.], (2) study of endwall film cooling using endwall film holes (document 2) [ Wang Ruidong, liu Cunliang, zhu Huiren. Endwall leakage flow cooling values study with bladed oblique downblow film holes [ C ]. Third eighteenth technical communication with third professional information network of china aerospace and second power joint conference of air days ]. Under the effect of rotation in an actual aeroengine working state, leakage outflow has stronger circumferential non-uniformity, and the gas film cooling efficiency of the end wall leakage flow is obviously lower than that of the existing related research of purge flow (slit jet) on a static test bed. The use of the diversion structure is to divert the sealed cold air to a position without gas invasion, and promote the cooling efficiency of the leakage flow gas film of the end wall of the turbine guider on the premise of not increasing the consumption of the cold air. The use of the relevant flow directing structure on the turbine guide is not seen in the published patent or journal literature.
Document 3[ Zeyu, luo Xiang, hu Yanwen, etc. ] experimental study of the impact of the frontal area of a bulge on the sealing efficiency of different rim sealing structures [ J ]. A push technique, 40 (5) ] describes a bulge structure, by installing the bulge structure on the wall of a turntable in the cavity structure of a turbine rotary disk, the frontal area of the cavity of the rotary disk is increased, and by acting on the fluid inside the cavity of the rotary disk by the bulge, the fluid under the same working condition has higher tangential velocity, the total pressure of the fluid is increased, so that the sealing effect in the cavity structure of the rotary disk is improved without increasing sealing cold air. This is different from the installation position and the principle of use of triangular pyramid type flow guiding structure described in this patent. The bulge structure introduced in the document [3] is arranged on the rotating wall surface in the cavity structure of the rotating disc, and the triangular pyramid-shaped flow guiding structure is arranged on the static wall surface of the turbine guider in the cavity structure of the rotating disc; the protruding structure that document [3] introduced reaches the purpose that improves the sealed effect in rotary disk chamber through the acting of rotary disk intracavity fluid, this patent triangular pyramid-shaped water conservancy diversion structure is then through guiding the leakage flow, will seal the cold air drainage to the position that does not have the gas invasion, has increased the leakage flow that flows from turbine director cascade passageway upper reaches, has improved the whole cooling efficiency of turbine director end wall.
In addition, chinese patent application, application number: CN202011469232.3 discloses a triangular prism-shaped flow guiding structure applied to a half split joint of a blade trailing edge, and in the prior art, the triangular prism-shaped flow guiding structure is arranged on the downstream wall of the half split joint to generate a turbulent flow effect on a cooling air film, so that the non-uniformity of the distribution of the air film on the downstream of the half split joint is obviously weakened, the spreading coverage effect and cooling efficiency of the cooling air film are improved, and the maximum temperature and the temperature gradient of the trailing edge are reduced. This is different from the installation position and the principle of use of triangular pyramid type flow guiding structure described in this patent. The triangular prism-shaped flow guiding structure in the prior art is arranged at the half split joint of the tail edge of the turbine blade, and the triangular prism-shaped flow guiding structure is arranged on the static wall surface of the turbine guide in the cavity of the rotating disc; above-mentioned triangular prism type water conservancy diversion structure is showing through the vortex effect and is weakening half split seam low reaches air film and distributing the unevenness, promotes cooling air film exhibition to cover effect and cooling efficiency, realizes trailing edge maximum temperature and temperature gradient's reduction, this patent triangular prism type water conservancy diversion structure is then through guiding leaking the flow, will seal the air conditioning drainage to the position that does not have the gas invasion, has increased the leakage flow that flows from turbine director cascade passageway upper reaches, has improved turbine director end wall's adiabatic air film cooling efficiency.
Disclosure of Invention
In order to improve the defects of the existing turbine guide end wall cooling technology, the invention provides a triangular pyramid-shaped flow guiding structure applied to a turbine guide, which has the following technical scheme:
the utility model provides a triangular pyramid-shaped water conservancy diversion structure, is applied to the turbine director, characterized by: the four surfaces of the flow guiding structure are 2 isosceles triangles and 2 right triangles, the pointed end faces to the direction of the incoming flow of the sealed cold air, and the pointed end is positioned in the rotary disk cavity structure right in front of the front edge of the turbine guide vanes, and the number of the pointed end is consistent with the number of the turbine guide vanes. In actual use, the triangular pyramid-shaped flow guiding structure can be milled integrally with the turbine guider, or the triangular pyramid-shaped flow guiding structure can be connected with the turbine guider by bolts after a metal girdle with the triangular pyramid-shaped flow guiding structure is processed independently.
The invention also discloses a turbine guide, which comprises a triangular pyramid-shaped flow guiding structure and is characterized in that: the root wall surface of the turbine guide and the wall surface of the rotating turbine disk at the upstream of the turbine guide form a rotating disk cavity structure. In order to prevent high-temperature main stream gas from invading the rotary disk cavity structure and improve the service life of the turbine component, sealing cold air is introduced into the rotary disk cavity structure in the actual working state of the engine, and leakage flow is formed after the sealing cold air is converged into the main stream. The triangular pyramid-shaped flow guide structure is positioned on the side wall surface of the turbine guider in the cavity structure of the rotating disc, so that leakage flow can be guided to be more uniform, the attachment effect of the leakage flow on the end wall of the turbine guider is improved, and the air film cooling effect of the end wall is improved.
The height of the cool air outflow slot of the rotating disc cavity structure is H, the ratio of the height H of the triangular pyramid-shaped flow guiding structure to the height H of the cool air outflow slot is 0.5-1, and the ratio of the width x of the triangular pyramid-shaped flow guiding structure to the height H of the cool air outflow slot is 2-3. The minimum size of the triangular pyramid-shaped flow guiding structure is limited by the processing technology, the maximum size is limited by the rotating disc cavity structure, and the rotation can be influenced when the ratio is larger than 1. The minimum size of the triangular pyramid-shaped flow guiding structure width is limited by the flow guiding effect, the ratio is smaller than 2, the gas invasion area cannot be covered, and the flow guiding effect is poor; the maximum size is limited by the circumferential distance of the turbine guide end walls, and a ratio greater than 3 exceeds the circumferential distance of each turbine guide end wall, and the installation requirement that the number of the flow guiding structures is consistent with the number of the turbine guide blades cannot be met.
The invention has the beneficial effects that:
according to the turbine guide with the triangular pyramid-shaped guide structure, the triangular pyramid-shaped guide structure is arranged on the side wall surface of the turbine guide in the rotating disc cavity structure at the upstream of the turbine guide to guide and disturb leakage flow, so that leakage flow flowing out of the upstream of a blade grid channel of the turbine guide is increased, leakage flow loss caused by gas invasion is reduced, and the integral cooling efficiency of the end wall of the turbine guide is improved. The triangular pyramid-shaped flow guide structure is arranged at the cavity structure of the rotating disc, has the characteristics of simple structure, no interference to main flow and good cooling effect, and can be applied to various turbine guides.
Drawings
The present invention will be described below with reference to the drawings and embodiments.
Fig. 1 is an isometric view of the present invention. In the figure, the ox direction is the axial direction, the oy direction is the circumferential direction, and the oz direction is the radial direction.
Fig. 2 is a schematic diagram of an embodiment of the present invention. In the figure: the serial number 1 indicates a first-stage turbine rotary blade disc, the serial number 2 indicates a second-stage turbine guide, the serial number 3 indicates a triangular pyramid-shaped flow guiding structure, the serial number 4 indicates a rotary disc cavity sealing cold air inlet, and the serial number 5 indicates a second-stage turbine rotary blade disc. H is the cold air outflow slot height.
Fig. 3 is an isometric view of a triangular pyramid-shaped flow guiding structure according to the present invention.
Fig. 4 is a three-view diagram of a triangular pyramid-shaped flow guiding structure according to the present invention, in which (a) is a front view, (b) is a top view, and (c) is a right side view. h is the height of the triangular pyramid-shaped flow guiding structure, x is the width of the triangular pyramid-shaped flow guiding structure, and alpha is the angle of the apex angle of the triangular pyramid.
Fig. 5 shows a method of designing a turbine guide with a triangular pyramid-shaped flow guiding structure and a gas turbine thereof.
FIG. 6 is a graph comparing circumferential film cooling efficiency at the leading edge of a turbine guide with a triangular pyramid-shaped flow guiding structure with a conventional turbine guide blade.
FIG. 7 is a graph of average circumferential film cooling efficiency profiles for a turbine pilot with a triangular pyramid-shaped flow guide structure at different axial distances from a conventional turbine pilot.
Description of the embodiments
The invention is described in more detail below with reference to the accompanying drawings:
in this embodiment, the turbine guide with the triangular pyramid-shaped flow guiding structure described in this patent is shown in fig. 1. In the figure, the ox direction is the axial direction, the oy direction is the circumferential direction, and the oz direction is the radial direction.
Fig. 2 is a schematic diagram of an embodiment of the present invention. In the figure: the serial number 1 indicates a first-stage turbine rotary blade disc, the serial number 2 indicates a second-stage turbine guide, the serial number 3 indicates a triangular pyramid-shaped flow guiding structure, the serial number 4 indicates a rotary disc cavity sealing cold air inlet, and the serial number 5 indicates a second-stage turbine rotary blade disc. H is the cold air outflow slot height. The sealing cold air of the disc cavity is injected into the disc cavity through the cold air inlet, the sealing cold air is converged into the main flow through the upstream of the secondary turbine guide to form leakage flow, and air film cooling is carried out on the end wall of the secondary turbine guide.
Fig. 3 is an isometric view of a triangular pyramid-shaped flow guiding structure according to the present invention. Fig. 4 is a three-view diagram of a triangular pyramid-shaped flow guiding structure according to the present invention, in which (a) is a front view, (b) is a top view, and (c) is a right side view. h is the height of the triangular pyramid-shaped flow guiding structure, x is the width of the triangular pyramid-shaped flow guiding structure, and alpha is the angle of the apex angle of the triangular pyramid. The triangular pyramid-shaped flow guiding structure is characterized in that: the device consists of 2 isosceles triangles and 2 right-angled triangles, wherein the pointed ends face to the direction of the incoming flow of the sealed cold air, are positioned in a rotating disc cavity structure right in front of the front edges of the blades of the turbine guide, are circumferentially arranged, and are consistent in number with the blades of the turbine guide. In actual use, the triangular pyramid-shaped flow guiding structure can be milled integrally with the turbine guider, or the triangular pyramid-shaped flow guiding structure can be connected with the turbine guider by bolts after a metal girdle with the triangular pyramid-shaped flow guiding structure is processed independently. In this embodiment, the cold air outflow slot height H is 4mm; the apex angle alpha of the triangular prism-shaped flow guiding structure is 90 degrees, the height h is 3mm, and the width x is 10.4mm. The ratio of the height H of the triangular pyramid-shaped flow guiding structure to the height H of the cold air outflow slot is 0.5-1, and the ratio of the width x of the triangular pyramid-shaped flow guiding structure to the height H of the cold air outflow slot is 2-3. In all the parameter ranges, the parameter selected in this embodiment is the median of the parameter ranges, which is a certain representative. In order to ensure comparability of results, the flow conditions of the turbine guide with the triangular pyramid-shaped flow guiding structure and the turbine guide without the flow guiding structure are completely consistent, and the geometrical structure is only different in whether the turbine guide is provided with the triangular pyramid-shaped flow guiding structure or not.
Fig. 5 is a design method of a turbine guide with triangular pyramid-shaped flow guiding structure and a gas turbine thereof, comprising the steps of:
step 1: the solid domain model finally applied to numerical simulation comprises a first-stage turbine rotary impeller, a second-stage turbine guider, a flow guiding structure and a second-stage turbine rotary impeller. The fluid domain model is obtained by subtracting the solid domain model from all the space contained by the turbine component. The sealing cold air of the disc cavity of the fluid domain model is injected into the disc cavity through the cold air inlet, the sealing cold air is converged into the main flow through the upstream of the secondary turbine guide to form leakage flow, and air film cooling is carried out on the end wall of the secondary turbine guide.
Step 2: and (3) generating unstructured grids for the solid domain model and the fluid domain model in the step one by using ICEM software, leading the grids into CFX software for solving, wherein boundary conditions are derived from a real gas turbine, a turbulence equation is selected from Reynolds average Navier-Stokes equation, and a turbulence model is selected from an SST model. The turbine guide endwall adiabatic film cooling efficiency is characterized by adding additional variables during the solution process, the turbulent flow scalar transport equation for the additional variables being:
wherein the method comprises the steps of
For the specific volume concentration of the tracer gas, +.>
Is a volume source item>
Is kinetic energy diffusion coefficient->
For turbulent concentration +.>
Is a turbulent schmitt number. Setting diffusion coefficient +.>
Correspond to->
Standard atmospheric pressure +.>
Diffusion coefficient in air, < >>
。
Step 3: extracting circumferential distribution and axial distribution of heat-insulating film cooling efficiency of the end wall of the turbine guide according to the logarithmic simulation result, comparing the heat-insulating film cooling efficiency of the turbine guide using a flow guiding structure with that of the end wall of the conventional turbine guide, and recording the result;
step 4: the height and length of the straight quadrangular prism of the flow guiding structure are adjusted within the parameter range, and the flow guiding structure has beneficial effects within the parameter range. In the design process, the effectiveness of the triangular pyramid-shaped flow guiding structure is verified mainly through numerical simulation calculation.
FIG. 6 is a graph comparing circumferential film cooling efficiency at the leading edge of a turbine guide with a triangular pyramid-shaped flow guiding structure with a conventional turbine guide blade. FIG. 6 is a graph of endwall adiabatic film cooling efficiency data taken with axial locations at the leading edge endwall stagnation points of turbine vane blades, but at different circumferential locations, showing the endwall adiabatic film cooling efficiency distribution of a turbine vane at the leading edge stagnation point along different circumferential locations. The abscissa in the figure is the dimensionless circumferential distance, Y is the circumferential distance of the actual data point from the left boundary, b is the circumferential length of one turbine guide blade end wall, Y/b=0 represents the circumferential position at the turbine guide left boundary (near the suction side), and Y/b=1 represents the circumferential position at the turbine guide right boundary (near the pressure side). The ordinate in the figure is leakage flow adiabatic film cooling efficiency at the end wall. It can be seen from the figure that the endwall leakage flow film is predominantly distributed on the suction side of the blade near the left boundary, with poor distribution on the leading edge and pressure side of the blade. In the figure, the broken line represents that the leakage flow heat-insulating air film cooling efficiency at the end wall of the conventional turbine guide without the triangular pyramid-shaped flow guiding structure is distributed along the circumferential direction, the solid line represents that the leakage flow heat-insulating air film cooling efficiency at the end wall of the turbine guide with the triangular pyramid-shaped flow guiding structure is distributed along the circumferential direction, and the difference between the two structures is only whether the triangular pyramid-shaped flow guiding structure is used or not. As can be seen from the comparison of the broken line and the solid line in the figure, the triangular pyramid-shaped flow guide structure is used for obviously improving the cooling efficiency of the heat-insulating air film of the end wall leakage flow on the suction surface side.
FIG. 7 is a graph of average circumferential film cooling efficiency profiles for a turbine pilot with a triangular pyramid-shaped flow guide structure at different axial distances from a conventional turbine pilot. FIG. 7 is an averaged view of leakage flow adiabatic film cooling efficiency data for each turbine guide endwall axial position. The distribution rule of the turbine guide end wall leakage flow heat insulation air film cooling efficiency along different axial positions is shown. The abscissa in the figure is the dimensionless axial distance, X is the axial distance of the actual data point from the boundary, C is the axial length of one turbine guide blade endwall, X/c=0 represents the axial position at the turbine guide forward boundary, and X/c=1 represents the axial position at the turbine guide aft boundary. In the figure, the broken line shows that the leakage flow heat-insulating air film cooling efficiency at the end wall of the conventional turbine guide without the triangular pyramid-shaped flow guiding structure is distributed along the axial direction, the solid line shows that the leakage flow heat-insulating air film cooling efficiency at the end wall of the turbine guide with the triangular pyramid-shaped flow guiding structure is distributed along the axial direction, and the difference between the two structures is only whether the triangular pyramid-shaped flow guiding structure is used or not. As can be seen from the comparison of the broken line and the solid line in the figure, the leakage flow heat insulation air film cooling efficiency at the end wall of the turbine guide is obviously improved by using the triangular pyramid-shaped flow guiding structure.
Fig. 6 and 7 compare the adiabatic film cooling efficiency of the turbine guide end wall with the triangular pyramid-shaped flow guide structure with the adiabatic film cooling efficiency of the turbine guide end wall without the flow guide structure. By comparison, the leakage flow heat insulation air film cooling efficiency at the end wall of the turbine guider is obviously improved by using the triangular pyramid-shaped flow guiding structure.
The foregoing has shown and described the basic principles, principal features and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present invention, and various changes and modifications may be made therein without departing from the spirit and scope of the invention, which is defined by the appended claims. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (1)
1. The design method of the gas turbine of the turbine guider with triangular pyramid type flow guiding structure, including the turbine guider, the turbine guider includes triangular pyramid type flow guiding structure, the triangular pyramid type flow guiding structure is made up of 2 isosceles triangles and 2 right triangles, the tip is towards the direction of flow of the sealed cold air, locate in front of blade leading edge of the turbine guider, the side wall of the turbine guider in the cavity structure of the rotary disk, arrange circumferentially; the number of the triangular pyramid-shaped flow guiding structures is consistent with that of the turbine guide vanes; the triangular pyramid-shaped flow guiding structure and the turbine guider are integrally milled; the method is characterized in that: the root wall surface of the turbine guide and the upstream rotating turbine disc wall surface form a rotating disc cavity structure, and the triangular pyramid-shaped flow guiding structure is positioned on the side wall surface of the turbine guide in the rotating disc cavity structure at the upstream of the turbine guide; the triangular pyramid-shaped flow guiding structures consist of 2 isosceles triangles and 2 right triangles, the pointed ends face to the direction of the cold air inflow, each triangular pyramid-shaped flow guiding structure is positioned right in front of the front edge of the turbine guide vane, and the number of the triangular pyramid-shaped flow guiding structures is consistent with that of the turbine guide vane; the height H of the cool air outflow slot of the cavity structure of the rotating disc is 4mm; the ratio of the height H of the triangular pyramid to the height H of the cool air outflow slot is 0.5-1, and the ratio of the width x of the triangular pyramid to the height H of the cool air outflow slot is 2-3, and the design method of the turbine guide with the triangular pyramid-shaped flow guiding structure is characterized in that: the method comprises the following steps:
step 1: aiming at the decryption and simplification of a certain type of gas turbine, a solid domain model finally applied to numerical simulation comprises a first-stage turbine rotary blade disc, a second-stage turbine guider, a triangular pyramid-shaped flow guiding structure and a second-stage turbine rotary blade disc; obtaining a fluid domain model by subtracting the solid domain model from all of the space contained by the turbine component; sealing cold air in a disc cavity of the fluid domain model is injected into the disc cavity through a cold air inlet, the sealing cold air is converged into a main flow from the upstream of the secondary turbine guider to form leakage flow, and air film cooling is carried out on the end wall of the secondary turbine guider;
step 2: generating unstructured grids by using ICEM software for the solid domain model and the fluid domain model in the step 1, leading the grids into CFX software for solving, wherein boundary conditions are derived from a real gas turbine, a Reynolds average Naviet Kex equation is selected for a turbulence equation, and an SST model is selected for a turbulence model; the turbine guide endwall adiabatic film cooling efficiency is characterized by adding additional variables during the solution process, the turbulent flow scalar transport equation for the additional variables being:
step 3: extracting circumferential distribution and axial distribution of heat-insulating film cooling efficiency of the end wall of the turbine guide according to the logarithmic simulation result, comparing the heat-insulating film cooling efficiency of the end wall of the turbine guide using the triangular pyramid-shaped flow guiding structure with that of the conventional turbine guide, and recording the result; the specific process is as follows:
the circumferential axial taking position is positioned at the standing point of the front edge end wall of the turbine guide vane, the end wall heat insulation film cooling efficiency data at different circumferential positions are plotted, the distribution rule of the end wall heat insulation film cooling efficiency of the turbine guide vane at the standing point of the front edge along different circumferential positions is shown, the abscissa is set to be a dimensionless circumferential distance, Y is the circumferential distance from the actual data point to the left boundary, b is the circumferential length of the end wall of the turbine guide vane, Y/b=0 represents the circumferential position at the position of the turbine guide vane left close to the suction surface boundary, and Y/b=1 represents the circumferential position at the position of the turbine guide vane right close to the pressure surface boundary; the ordinate is leakage flow heat insulation air film cooling efficiency at the end wall; the broken line shows that the leakage flow heat-insulating air film cooling efficiency at the end wall of the conventional turbine guide without the triangular pyramid-shaped flow guiding structure is distributed along the circumferential direction, and the solid line shows that the leakage flow heat-insulating air film cooling efficiency at the end wall of the turbine guide with the triangular pyramid-shaped flow guiding structure is distributed along the circumferential direction;
the average circumferential air film cooling efficiency distribution curve of the turbine guide with the triangular pyramid-shaped flow guide structure at different axial distances from the conventional turbine guide is obtained by averaging leakage flow heat insulation air film cooling efficiency data of the axial position of the end wall of each turbine guide, and the distribution rule of the leakage flow heat insulation air film cooling efficiency of the end wall of the turbine guide along different axial positions is shown; the abscissa is the dimensionless axial distance, X is the axial distance of the actual data point from the boundary, C is the axial length of one turbine guide blade end wall, X/c=0 represents the axial position at the turbine guide forward boundary, and X/c=1 represents the axial position at the turbine guide aft boundary; the broken line shows that the leakage flow heat-insulating air film cooling efficiency at the end wall of the conventional turbine guide without the triangular pyramid-shaped flow guiding structure is distributed along the axial direction, the solid line shows that the leakage flow heat-insulating air film cooling efficiency at the end wall of the turbine guide with the triangular pyramid-shaped flow guiding structure is distributed along the axial direction, and the difference between the two structures is only whether the triangular pyramid-shaped flow guiding structure is used or not;
step 4: and the triangular pyramid height and width of the triangular pyramid type flow guiding structure are adjusted within the parameter range, and the beneficial effects of the triangular pyramid type flow guiding structure within the parameter range are verified.
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