CN114412579B - Splayed rib guide structure, turbine guide and gas turbine design method - Google Patents
Splayed rib guide structure, turbine guide and gas turbine design method Download PDFInfo
- Publication number
- CN114412579B CN114412579B CN202210090476.3A CN202210090476A CN114412579B CN 114412579 B CN114412579 B CN 114412579B CN 202210090476 A CN202210090476 A CN 202210090476A CN 114412579 B CN114412579 B CN 114412579B
- Authority
- CN
- China
- Prior art keywords
- turbine
- guide
- splayed
- turbine guide
- end wall
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The splayed rib flow guiding structure consists of a pair of axisymmetric straight quadrangular prisms similar to the splayed shape. In the rotating disk cavity structure located right in front of the leading edge of the turbine guide blades, the number of the rotating disk cavity structure is circumferentially arranged to be consistent with the number of the turbine guide blades. The splayed guide structure can be milled integrally with the turbine guide, or the splayed guide structure can be connected with the turbine guide by bolts after a metal ring belt with the splayed guide structure is independently processed. According to the turbine guide with the splayed rib flow guiding structure, disclosed by the invention, the splayed 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 invention arranges the splayed rib flow guiding structure at the cavity structure of the rotating disc, has the characteristics of simple structure, no interference to the main flow and good cooling effect, and can be applied to various turbine directors.
Description
Technical Field
The invention belongs to the technical field of cooling of turbine blades of gas turbines, and discloses a turbine guide with an splayed rib flow guiding structure and application thereof.
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) [ raydong, liu Cunliang, zhu Huiren. Endwall leakage flow cooling values study with oblique downblowing film holes of the blade body [ C ]. Third eighteenth technical communication of third professional information network of china aerospace and second power joint conference of the 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 use principle of the splayed rib diversion structure. 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 splayed rib guide structure is arranged on the 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 acting of rotary disk intracavity fluid, and this patent "eight" style of calligraphy rib 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: CN202011467794.4 discloses a double-guide rib guide structure applied to a half split joint of a turbine blade trailing edge, and in the prior art, a turbulent flow effect is generated by arranging double-guide ribs on the downstream wall of the half split joint to face a cooling air film, so that the non-uniformity of the distribution of the air film at the downstream of the half split joint is obviously weakened, the circumferential coverage effect and the 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 use principle of the splayed flow guiding structure. The double-guide-rib guide structure in the prior art is arranged at the half split joint of the tail edge of the turbine blade, and the eight-shaped guide structure is arranged on the static wall surface of the turbine guide in the cavity of the rotating disc; above-mentioned prior art's two water conservancy diversion rib water conservancy diversion structures are showing and are weakening half split seam low reaches air film distribution non-uniformity through the vortex effect, promote air film circumference and cover effect and cooling efficiency, realize trailing edge maximum temperature and temperature gradient's reduction, "eight" style of calligraphy water conservancy diversion structure is then through guiding the leakage 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 an eight-shaped rib flow guiding structure applied to a turbine guide, and the technical scheme is as follows:
an eight-shaped rib flow guiding structure is applied to a turbine guider and is characterized in that: is composed of a pair of straight quadrangular prisms which are axisymmetrically distributed and are shaped like an eight. The turbine guide blades are positioned right in front of the front edges of the turbine guide blades, and the side wall surfaces of the turbine guide in the cavity structure of the rotating disk are circumferentially arranged, and the number of the side wall surfaces is consistent with that of the turbine guide blades.
The invention also discloses a turbine guide, which comprises an eight-shaped rib 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 cavity of the rotary disk, the service life of the turbine component is prolonged, sealing cold air is introduced into the inner part of the cavity structure of the rotary disk 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 splayed rib flow guiding structure is positioned on the side wall surface of the turbine guider in the rotating disc cavity structure, can guide leakage flow to flow out from a position without gas invasion, improves the adhesion effect of the leakage flow on the end wall of the turbine guider, and further improves the air film cooling effect of the end wall. In actual use, the splayed flow guiding structure can be milled integrally with the turbine guide, or the splayed flow guiding structure can be independently processed into a metal ring belt and then connected with the turbine guide by bolts.
The height of the cold air outflow slot of the rotary disc cavity structure is H, the ratio of the height H of a single straight quadrangular prism of the splayed rib flow guiding structure to the height H of the cold air outflow slot is 0.5-1, the ratio of the length m of the straight quadrangular prism to the height H of the cold air outflow slot is 1-3, and the ratio of the width n of the straight quadrangular prism to the height H of the cold air outflow slot is 0.25-0.75. The minimum dimension of the height of the straight quadrangular prism is limited by the drainage effect, the drainage effect is poorer when the ratio is smaller than 0.5, the maximum dimension is limited by the cavity structure of the rotating disc, and the rotation can be influenced when the ratio is larger than 1. The minimum size of straight quadrangular length is limited by drainage effect, and the ratio is less than 1, can not cover gas invasion area, can not realize drainage effect very well, and the maximum size is limited by turbine director end wall circumference distance, and the ratio is greater than 3 and can surpass every turbine director end wall circumference distance, can not realize the installation requirement that water conservancy diversion structure quantity is unanimous with turbine director blade quantity. The smallest dimension of the width of the right quadrangular prism is limited by the processing technology, and the largest dimension is limited by the rotating disk cavity structure.
The invention also discloses a gas turbine, which comprises the turbine guide.
The invention also discloses a turbine guide with the splayed rib guide structure and a design method of the gas turbine of the turbine guide.
Advantageous effects
According to the turbine guide with the splayed rib guide structure, the splayed rib 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 invention arranges the splayed rib diversion structure at the rotary disk cavity structure, has the characteristics of simple structure, no interference to main flow and good cooling effect, and can be applied to various turbine guides.
Drawings
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, 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 an eight-shaped rib 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 an "eight" shaped flow guiding structure according to the present invention.
Fig. 4 is a three-view diagram of an "eight" shaped flow guiding structure according to the present invention, wherein (a) is a front view, (b) is a top view, and (c) is a left side view. m is the length of a straight quadrangular prism, n is the width of the straight quadrangular prism, and h is the height of the straight quadrangular prism.
FIG. 5 is a method of designing a turbine guide with an inverted V-shaped rib guide structure and a gas turbine thereof.
FIG. 6 is a graph of circumferential film cooling efficiency versus a conventional turbine guide vane having an inverted V-shaped flow guide configuration.
FIG. 7 is a graph of average circumferential film cooling efficiency profiles for a turbine pilot with an "eight" shaped flow guide structure at different axial distances from a conventional turbine pilot.
Description of the embodiments
Embodiments of the invention are described in more detail below with reference to the attached drawing figures:
the turbine guide with the splayed flow guide structure is shown in fig. 1, wherein the ox direction is the axial direction, the oy direction is the circumferential direction, and the oz direction is the radial direction.
FIG. 3 is an isometric view of an "eight" shaped flow guiding structure according to the present invention. Fig. 4 is a three-view diagram of an "eight" shaped flow guiding structure according to the present invention, wherein (a) is a front view, (b) is a top view, and (c) is a left side view. m is the length of a straight quadrangular prism, n is the width of the straight quadrangular prism, and h is the height of the straight quadrangular prism. The eight-shaped rib flow guiding structure is applied to the turbine guider, a rotary disk cavity structure is formed by the root wall surface of the turbine guider and the upstream rotary turbine disk wall surface, and the eight-shaped rib flow guiding structure is positioned on the side wall surface of the turbine guider in the upstream rotary disk cavity structure of the turbine guider. The eight-shaped rib flow guiding structures are formed by a pair of axisymmetric straight quadrangular columns which are similar to the eight in shape, each eight-shaped rib flow guiding structure is positioned right in front of the front edge of the blade, and the number of the eight-shaped rib flow guiding structures is consistent with that of the blades of the turbine guider. In the embodiment, the height H of the cool air outflow slot of the rotating disc cavity structure is 4mm; the length of the straight quadrangular prism is 8mm, the width is 2mm, and the height is 3mm. The ratio of the height H of a single straight quadrangular prism with the eight-shaped rib flow guiding structure to the height H of the cold air outflow slot is 0.5-1, the ratio of the length m of the straight quadrangular prism to the height H of the cold air outflow slot is 1-3, and the ratio of the width n of the straight quadrangular prism to the height H of the cold air outflow slot is 0.25-0.75. The parameter selected in this embodiment is a median value of the parameter range, which is a certain representative. In order to ensure comparability of results, the flow conditions of the turbine guide with the splayed flow guiding structure and the turbine guide without the flow guiding structure are completely consistent, and the geometrical structure is only different in that whether the turbine guide is provided with the splayed flow guiding structure or not. Due to the existence of the eight-shaped flow guiding structure, more sealing cold air flows to the area without gas invasion, and the integral cooling efficiency of the end wall of the turbine guide is improved.
FIG. 5 is a schematic illustration of a turbine guide with an "eight" rib guide structure and 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 impeller, a second-stage turbine guider, a flow guiding structure and a second-stage turbine rotating 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 end wall of the turbine guide using a diversion structure with that of the end wall of a 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 splayed rib flow guiding structure is verified mainly through numerical simulation calculation.
FIG. 6 is a graph of the efficiency of circumferential adiabatic film cooling versus a conventional turbine guide vane leading edge with an inverted V-shaped rib guide structure. 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 insulation air film cooling efficiency at the end wall of the conventional turbine guide without the splayed rib guide structure is distributed along the circumferential direction, and the solid line shows that the leakage flow heat insulation air film cooling efficiency at the end wall of the turbine guide with the splayed rib guide structure is distributed along the circumferential direction, and the difference between the two structures is only whether the splayed rib 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 splayed rib diversion structure obviously improves the cooling efficiency of the heat-insulating air film of the end wall leakage flow on the suction side.
FIG. 7 is an average circumferential film cooling efficiency profile for a turbine vane with an "eight" rib guide structure at different axial distances from a conventional turbine vane. 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 insulation air film cooling efficiency at the end wall of the conventional turbine guide without the splayed rib guide structure is distributed along the axial direction, the solid line shows that the leakage flow heat insulation air film cooling efficiency at the end wall of the turbine guide with the splayed rib guide structure is distributed along the axial direction, and the difference between the two structures is only whether the splayed rib 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 splayed rib guide structure obviously improves the cooling efficiency of the leakage flow heat insulation air film at the end wall of the turbine guider.
Fig. 6 and 7 compare the adiabatic film cooling efficiency of the turbine guide end wall with the "splayed" rib guide structure with the adiabatic film cooling efficiency of the turbine guide end wall without the guide structure. As can be seen by comparison, the use of the splayed rib guide structure significantly improves the cooling efficiency of the leakage flow insulating film at the end wall of the turbine guide.
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 the splayed rib guiding structure comprises the turbine guider, wherein the turbine guider comprises the splayed rib guiding structure, and the splayed rib guiding structure is formed by a pair of straight quadrangular prisms which are axisymmetrically distributed and are similar to the splayed shape; the turbine guide side wall surface in the cavity structure of the rotating disc is arranged circumferentially and is positioned right in front of the front edge of the turbine guide blade; the number of the splayed rib guide structures is consistent with that of the turbine guide vanes; the splayed 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 splayed rib 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 splayed rib guide structures are formed by a pair of axisymmetrically distributed straight quadrangular columns similar to the shape of an splayed, and each splayed rib guide structure is positioned right in front of the front edge of each blade and circumferentially arranged, and the number of the splayed rib guide structures is consistent with that of the blades of the turbine guider; the height H of the cool air outflow slot of the cavity structure of the rotating disc is 4mm; the length of the straight quadrangular prism is 8mm, the width is 2mm, and the height is 3mm; the ratio of the height H of the single straight quadrangular prism of the splayed rib flow guiding structure to the height H of the cold air outflow slot is 0.5-1, the ratio of the length m of the straight quadrangular prism to the height H of the cold air outflow slot is 1-3, the ratio of the width n of the straight quadrangular prism to the height H of the cold air outflow slot is 0.25-0.75, and the splayed rib 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 vane disc, a second-stage turbine guide, a splayed rib guide structure and a second-stage turbine rotary vane 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: and extracting circumferential distribution and axial distribution of heat-insulating film cooling efficiency of the end wall of the turbine guide by using a logarithmic value simulation result, comparing the heat-insulating film cooling efficiency of the end wall of the turbine guide and the heat-insulating film cooling efficiency of the end wall of the conventional turbine guide by using a splayed rib guide structure, and recording the result:
the method comprises the steps of (1) drawing end wall heat insulation air film cooling efficiency data of the turbine guide vane at axial positions at the stagnation points of the front edge end walls of the turbine guide vane and at different circumferential positions, and displaying the distribution rule of the end wall heat insulation air film cooling efficiency of the turbine guide vane at the stagnation points of the front edge along the different circumferential positions; setting the abscissa as a dimensionless circumferential distance, Y being the circumferential distance of the actual data point from the left boundary, b being the circumferential length of one turbine guide blade end wall, Y/b=0 representing that the circumferential position is close to the suction surface at the turbine guide left boundary, Y/b=1 representing that the circumferential position is close to the pressure surface at the turbine guide right 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 splayed rib guide 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 splayed rib guide structure is distributed along the circumferential direction;
the average circumferential air film cooling efficiency distribution curve of the turbine guide with the splayed rib 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 film cooling efficiency at the end wall of the conventional turbine guide without the splayed flow 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 splayed flow guide structure is distributed along the axial direction;
step 4: the height and the length of the straight quadrangular prism of the splayed rib flow guiding structure are adjusted within the parameter range, and the splayed rib flow guiding structure within the parameter range is verified to have beneficial effects.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210090476.3A CN114412579B (en) | 2022-01-25 | 2022-01-25 | Splayed rib guide structure, turbine guide and gas turbine design method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210090476.3A CN114412579B (en) | 2022-01-25 | 2022-01-25 | Splayed rib guide structure, turbine guide and gas turbine design method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114412579A CN114412579A (en) | 2022-04-29 |
| CN114412579B true CN114412579B (en) | 2023-05-05 |
Family
ID=81276627
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210090476.3A Active CN114412579B (en) | 2022-01-25 | 2022-01-25 | Splayed rib guide structure, turbine guide and gas turbine design method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114412579B (en) |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP5283855B2 (en) * | 2007-03-29 | 2013-09-04 | 株式会社Ｉｈｉ | Turbomachine wall and turbomachine |
| JP2015229981A (en) * | 2014-06-06 | 2015-12-21 | 三菱日立パワーシステムズ株式会社 | Axial flow turbine stationary blade |
| CN109854307B (en) * | 2019-03-13 | 2020-10-16 | 北京航空航天大学 | Turbine bulge sealing structure |
| CN112459852B (en) * | 2020-12-14 | 2021-09-24 | 北京航空航天大学 | Be applied to two water conservancy diversion rib water conservancy diversion structures of turbine blade trailing edge half-splitting seam |
-
2022
- 2022-01-25 CN CN202210090476.3A patent/CN114412579B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN114412579A (en) | 2022-04-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US5352087A (en) | Cooling fluid ejector | |
| US6254333B1 (en) | Method for forming a cooling passage and for cooling a turbine section of a rotary machine | |
| Green et al. | Ingestion into the upstream wheelspace of an axial turbine stage | |
| JP5911677B2 (en) | Turbine assembly having end wall profiled airfoils and selective clocking | |
| US20170248155A1 (en) | Centrifugal compressor diffuser passage boundary layer control | |
| JP2014532831A (en) | Asymmetric radial spline seals for gas turbine engines | |
| CN112160943A (en) | Anti-surge structure of compressor casing of gas turbine and surge margin evaluation method thereof | |
| JP2011179500A (en) | Cooling gas turbine components with seal slot channels | |
| CN112459852B (en) | Be applied to two water conservancy diversion rib water conservancy diversion structures of turbine blade trailing edge half-splitting seam | |
| CN108442985B (en) | Slot cooling structure capable of improving cooling efficiency of end wall of stationary blade channel | |
| Yang et al. | Numerical prediction of film cooling and heat transfer with different film-hole arrangements on the plane and squealer tip of a gas turbine blade | |
| CN215633160U (en) | Turbine cooling seal air supply structure and aircraft engine | |
| CN114412579B (en) | Splayed rib guide structure, turbine guide and gas turbine design method | |
| Liu et al. | Numerical investigations of flow features in a low pressure steam turbine last stage under different mass flow rates | |
| Bringhenti et al. | Effects of turbine tip clearance on gas turbine performance | |
| Wang et al. | Influence of secondary sealing flow on performance of turbine axial rim seals | |
| JP2019011756A (en) | Rotor blade for turbo machine | |
| CN114439552B (en) | Triangular pyramid-shaped flow guiding structure, turbine guider and gas turbine design method thereof | |
| CN114412578B (en) | Cylindrical flow guiding structure, turbine guide and gas turbine design method | |
| Chen et al. | Numerical investigation of the centrifugal compressor stability improvement by half vaned low solidity diffusers | |
| Yang et al. | Controlling Leakage Flows Over a Rotor Blade Tip Using Air-Curtain Injection: Part I—Aero-Thermal Performance of Rotor Tips | |
| CN115906430A (en) | Axial flow compressor labyrinth leakage loss prediction method | |
| CN112343667B (en) | Continuous V-shaped rib flow guide structure applied to turbine blade trailing edge half-splitting seam | |
| Zhang et al. | Internal flow characteristics of a variable mixed flow turbine with partially-rotating vane nozzle | |
| CN114151141B (en) | Aeroengine turbine disk cavity gas collection flow guide structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |