CN114412578B - Cylindrical flow guiding structure, turbine guide and gas turbine design method - Google Patents
Cylindrical flow guiding structure, turbine guide and gas turbine design method Download PDFInfo
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- CN114412578B CN114412578B CN202210090454.7A CN202210090454A CN114412578B CN 114412578 B CN114412578 B CN 114412578B CN 202210090454 A CN202210090454 A CN 202210090454A CN 114412578 B CN114412578 B CN 114412578B
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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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- Engineering & Computer Science (AREA)
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- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The cylindrical flow guiding structure is cylindrical in geometric shape, is positioned in the rotary disk cavity structure right in front of the front edge of the guide vanes, is circumferentially arranged, and is consistent with the number of the turbine guide vanes. In actual use, the cylindrical flow guiding structure can be milled integrally with the turbine guide, or the cylindrical flow guiding structure can be connected with the turbine guide by bolts after a metal girdle with the cylindrical flow guiding structure is independently processed. According to the turbine guide with the cylindrical guide structure, the cylindrical guide structure is arranged on the side wall surface of the guide in the rotary disc cavity structure positioned at the upstream of the turbine guide, so that the leakage flow of the rim is guided and disturbed, the leakage flow loss caused by gas invasion is reduced, and the integral cooling efficiency of the end wall of the guide is improved. The cylindrical 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.
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 cylindrical guide structure and application thereof.
Background
A gas turbine engine is a thermodynamic device based on the brayton cycle, which, by virtue of its powerful output power and high thermal efficiency, has 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 metrics, advanced gas turbine engines may have a pre-turbine temperature of 1800-2100K, while turbine blade materials have a temperature tolerance limit far less than turbine inlet temperatures, where the temperature differentials present can only be addressed by complex blade cooling and thermal barrier coating techniques. 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) endwall leakage flow cooling values study using endwall film holes [ Wang Ruidong, liu Cunliang, zhu Huiren ] endwall leakage flow cooling values study with bladed oblique downblow film holes [ C ]. Third professional information net of chinese aerospace third eighteenth technical communication conference and second joint conference of air-space power ]. 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 cylindrical flow guiding structure is used for guiding the sealed cold air to a position without gas invasion, and the leakage flow air film cooling efficiency of the end wall of the turbine guide is improved on the premise of not increasing the cold air consumption. The use of a related cylindrical flow guiding structure on a 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 use principle of the cylindrical flow guiding structure. The bulge structure introduced in the document [3] is arranged on a rotating wall surface in a cavity structure of the rotating disc, and the cylindrical flow guiding structure is arranged on a static wall surface of the turbine guide in the cavity 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 work of rotating disk intracavity portion fluidic, this patent cylindrical 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: CN202011467795.9 discloses a corrugated rib guide structure applied to a half split seam of a turbine blade trailing edge, and in the prior art, a turbulent flow effect is generated by arranging double guide ribs on a downstream wall of the half split seam to face a cooling air film, so that uneven distribution of the air film at the downstream of the half split seam is obviously weakened, circumferential coverage effect and cooling efficiency of the cooling air film are improved, and the maximum temperature and temperature gradient of the trailing edge are reduced. This is different from the installation position and the use principle of the cylindrical flow guiding structure. The corrugated rib guide structure in the prior art is arranged at the half split joint of the tail edge of the turbine blade, and the cylindrical guide structure is arranged on the static wall surface of the turbine guide in the cavity of the rotating disc; above-mentioned corrugated rib water conservancy diversion structure among the prior art is showing and is weakening half split seam low reaches air film distribution non-uniformity through the vortex effect, promotes cooling air film circumference and covers effect and cooling efficiency, realizes trailing edge maximum temperature and temperature gradient's reduction, this patent cylindrical 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 blade cascade passageway upper reaches, has improved turbine director end wall's overall cooling efficiency.
Disclosure of Invention
In order to improve the defects of the existing turbine guide end wall cooling technology, the invention provides a cylindrical flow guiding structure, which has the following technical scheme:
a cylindrical flow guiding structure is applied to a turbine guider and is characterized in that: the geometry is a cylinder, which is located just in front of the leading edge of the turbine guide blades, and is circumferentially arranged in a number consistent with the number of turbine guide blades.
The invention also discloses a turbine guide, which comprises a cylindrical flow guiding structure and is characterized in that: the turbine guide root wall forms a rotating disk cavity structure with the rotating turbine disk wall upstream of the turbine guide. In order to prevent high-temperature main stream gas from invading the inner part of the rotary disk cavity and improve the service life of the turbine component, sealing cold air is introduced into the inner part of the rotary disk cavity 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 cylindrical 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. In actual use, the cylindrical flow guiding structure can be milled integrally with the turbine guide, or the cylindrical flow guiding structure can be connected with the turbine guide by bolts after a metal girdle with the cylindrical flow guiding structure is independently processed.
The height of the cold air outflow slot of the rotary disc cavity structure is H, the ratio of the height of the cylindrical flow guiding structure to the height H of the cold air outflow slot is 0.5-1, and the ratio of the diameter of the cylindrical flow guiding structure to the height H of the cold air outflow slot is 1-3. The minimum dimension of the cylinder height is limited by the machining process and the maximum dimension is limited by the rotating disk cavity structure, with greater than 1 affecting rotation. The minimum dimension of the diameter of the cylinder is limited by the drainage effect, and the ratio is smaller than 1, so that the gas invasion area cannot be covered; the maximum size is limited by the circumferential distance of the end walls of the turbine guide, and the length ratio of more than 3 exceeds the circumferential distance of the end walls of each turbine guide, so that the installation requirement that the number of the cylindrical guide structures is consistent with the number of the blades of the turbine guide cannot be realized.
According to the turbine guide with the cylindrical guide structure, the cylindrical 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 the rim leakage flow, so that the leakage flow flowing out of the upstream of the blade grid channel of the turbine guide is increased, the leakage flow energy loss caused by gas invasion is reduced, and the integral cooling efficiency of the end wall of the turbine guide is improved. The cylindrical 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, wherein: the number 6 refers to the leading edge stagnation point.
FIG. 2 is a schematic diagram of an embodiment of the present invention, wherein: 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 cylindrical 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. And H is the height of the sealed cool air outflow slot.
Fig. 3 is an isometric view of a cylindrical flow guiding structure according to the present invention.
Fig. 4 is a three-view of a cylindrical flow guiding structure according to the present invention. Wherein, (a) is a front view, (b) is a top view, and (c) is a left view; h is the height of the cylindrical flow guiding structure, and D is the diameter of the cylindrical flow guiding structure.
FIG. 5 is a method of designing a turbine guide with a cylindrical flow guiding structure and a gas turbine thereof.
FIG. 6 is a graph of the comparison of circumferential adiabatic film cooling efficiency at the leading edge of a turbine guide with a cylindrical flow guiding structure and a conventional turbine guide blade.
FIG. 7 is a graph of average circumferential adiabatic film cooling efficiency profiles for a turbine guide with a cylindrical flow guiding structure at different axial distances from a conventional turbine guide.
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 cylindrical flow guiding structure described in this patent is shown in fig. 1.
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 cylindrical 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 cylindrical flow guiding structure according to the present invention. Fig. 4 is a three-view of a cylindrical flow guiding structure according to the present invention. Wherein, (a) is a front view, (b) is a top view, and (c) is a left view; h is the height of the cylindrical flow guiding structure, and D is the diameter of the cylindrical flow guiding structure. The cylindrical flow guiding structure is characterized in that: the geometry is a cylinder, and the cylinder is arranged circumferentially in the cavity structure of the rotating disk just in front of the front edge of the turbine guide vanes, and the number of the cylinder is consistent with that of the turbine guide vanes. When in actual use, the cylindrical flow guiding structure can be milled integrally with the turbine guider, or the metal girdle with the cylindrical flow guiding structure can be processed independently and then connected with the turbine guider by using bolts. In this embodiment, the cold air outflow slot height H is 4mm; the diameter D of the cylindrical flow guiding structure is 8mm, and the height h is 3mm. According to the invention, the ratio of the cylinder height H of the cylindrical flow guiding structure to the cold air outflow slot height H is 0.5-1, and the ratio of the cylinder diameter D to the cold air outflow slot height H is 1-3. In all the parameter ranges, the parameter selected in this embodiment is the median of the parameter ranges, which is a certain representative. To ensure comparability of the results. The turbine guide with the cylindrical flow guiding structure and the turbine guide without the cylindrical flow guiding structure have the same flow conditions, and the geometric structure only differs in that whether the turbine guide is provided with the cylindrical flow guiding structure or not.
FIG. 5 is a schematic illustration of a turbine pilot with a cylindrical flow guiding structure and a method of designing a gas turbine thereof, including the steps of:
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 rotating blade disc, a second-stage turbine guider, a cylindrical flow guiding structure and a second-stage turbine rotating blade disc; 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 (1)>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 when solvingCorrespond 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 end wall of the turbine guide using a cylindrical flow guiding structure with that of the conventional turbine guide, and recording the result;
step 4: the cylindrical height and diameter of the cylindrical flow guiding structure are adjusted within the parameter range, and the cylindrical flow guiding structure within the parameter range is verified to have beneficial effects. In the design process, the effectiveness of the cylindrical flow guiding structure is verified mainly through numerical simulation calculation.
FIG. 6 is a graph of the comparison of circumferential adiabatic film cooling efficiency at the leading edge of a turbine guide with a cylindrical flow guiding structure and 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 shows that the leakage flow heat-insulating air film cooling efficiency at the end wall of the conventional turbine guide without the cylindrical 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 cylindrical flow guiding structure is distributed along the circumferential direction, and the difference between the two structures is only whether the cylindrical 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 use of the cylindrical flow guiding structure obviously improves the cooling efficiency of the heat insulation film of the end wall leakage flow on the suction surface side.
FIG. 7 is an average circumferential film cooling efficiency profile for a turbine guide with a cylindrical flow guiding structure at different axial distances from a conventional turbine guide. 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 cylindrical guide 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 cylindrical guide structure is distributed along the axial direction, and the difference between the two structures is only whether the cylindrical guide structure is used or not. As can be seen from the comparison of the broken line and the solid line in the figure, the use of the cylindrical flow guiding structure significantly improves the cooling efficiency of the leakage flow heat insulation film at the end wall of the turbine guide.
Fig. 6 and 7 compare the adiabatic film cooling efficiency of the turbine guide end wall with the cylindrical guide structure with the adiabatic film cooling efficiency of the turbine guide end wall without the cylindrical guide structure, and by comparing, it can be seen that the use of the cylindrical guide structure significantly improves the leakage flow adiabatic film cooling efficiency at the turbine guide end wall.
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 cylindrical flow guiding structure, including the turbine guider, the turbine guider includes the cylindrical flow guiding structure, the cylindrical flow guiding structure locates in front of blade leading edge of the turbine guider, the turbine guider sidewall in the cavity structure of the rotary disk, arrange circumferentially; the number of the cylindrical flow guiding structures is consistent with that of the turbine guide vanes; the cylindrical 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 cylindrical 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; each cylindrical flow guiding structure is positioned right in front of the front edge of the turbine guide vane, and is circumferentially arranged, and the number of the cylindrical flow guiding structures is consistent with that of the turbine guide vane; the height H of the cool air outflow slot of the rotating disc cavity structure is 4mm, the ratio of the height of the cylinder to the height H of the cool air outflow slot is 0.5-1, and the ratio of the diameter of the cylinder to the height H of the cool air outflow slot is 1-3; the design method of the turbine guide with the cylindrical flow guiding structure 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 rotating blade disc, a second-stage turbine guider, a cylindrical flow guiding structure and a second-stage turbine rotating 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:wherein->For the specific volume concentration of the tracer gas, +.>Is a volume source item>Is kinetic energy diffusion coefficient->For turbulent concentration +.>For the turbulence schmitt number, the diffusion coefficient is set in solving>Corresponding to 298K, CO at standard atmospheric pressure 2 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 end wall of the turbine guide using a cylindrical flow guiding structure with that of the conventional turbine guide, and recording the result; the specific process is as follows:
the comparison curve of the circumferential adiabatic film cooling efficiency at the front edge of the turbine guide with a cylindrical guide structure and the conventional turbine guide blade is made by taking the data of the adiabatic film cooling efficiency of the end wall, which are positioned at the standing point of the front edge of the turbine guide blade and are positioned at different circumferential positions, showing the distribution rule of the adiabatic film cooling efficiency of the end wall of the turbine guide at the standing point of the front edge along different circumferential positions, wherein the abscissa is 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 blade, Y/b=0 represents the circumferential position at the boundary of the turbine guide left close to the suction surface, and Y/b=1 represents the circumferential position at the boundary of the turbine guide right close to the pressure surface; 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 film cooling efficiency at the end wall of the conventional turbine guide without the cylindrical guide structure is distributed along the circumferential direction, and the solid line shows that the leakage flow heat-insulating film cooling efficiency at the end wall of the turbine guide with the cylindrical guide structure is distributed along the circumferential direction;
the average circumferential adiabatic air film cooling efficiency distribution curve of the turbine guide with the cylindrical flow guiding structure at different axial distances from the conventional turbine guide is obtained by averaging leakage flow adiabatic 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 adiabatic 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 vane endwall, X/c=0 represents the axial position at the 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 film cooling efficiency at the end wall of the conventional turbine guide without the cylindrical guide structure is distributed along the axial direction, and the solid line shows that the leakage flow heat-insulating film cooling efficiency at the end wall of the turbine guide with the cylindrical guide structure is distributed along the axial direction;
step 4: the cylindrical height and diameter of the cylindrical flow guiding structure are adjusted within the parameter range, and the cylindrical flow guiding structure within the parameter range is verified to have beneficial effects.
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| EP0502660A1 (en) * | 1991-03-04 | 1992-09-09 | General Electric Company | Platform assembly for attaching rotor blades to a rotor disk |
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2022
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0502660A1 (en) * | 1991-03-04 | 1992-09-09 | General Electric Company | Platform assembly for attaching rotor blades to a rotor disk |
| CA2321375A1 (en) * | 1999-09-30 | 2001-03-30 | Mitsubishi Heavy Industries, Ltd. | An arrangement for sealing a steam-cooled gas turbine |
| CN109854307A (en) * | 2019-03-13 | 2019-06-07 | 北京航空航天大学 | A kind of novel turbine protrusion seal structure |
| CN112523810A (en) * | 2020-12-14 | 2021-03-19 | 北京航空航天大学 | Triangular column type flow guide structure applied to turbine blade trailing edge half-splitting seam |
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| Title |
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