CN116085063A - Active wind shadow air film cooling structure for improving end wall cooling performance - Google Patents

Active wind shadow air film cooling structure for improving end wall cooling performance Download PDF

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Publication number
CN116085063A
CN116085063A CN202310299167.1A CN202310299167A CN116085063A CN 116085063 A CN116085063 A CN 116085063A CN 202310299167 A CN202310299167 A CN 202310299167A CN 116085063 A CN116085063 A CN 116085063A
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CN
China
Prior art keywords
cooling
active wind
wind shadow
end wall
air film
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CN202310299167.1A
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Chinese (zh)
Inventor
李军
栗智宇
张垲垣
李志刚
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Xian Jiaotong University
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Xian Jiaotong University
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Priority to CN202310299167.1A priority Critical patent/CN116085063A/en
Publication of CN116085063A publication Critical patent/CN116085063A/en
Pending legal-status Critical Current

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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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/72—Wind turbines with rotation axis in wind direction

Abstract

The invention discloses an active wind shadow air film cooling structure capable of improving the cooling performance of the end wall of a first-stage stator blade of a turbine. During operation, cooling air is introduced from the bottom of the chamber and enters the main flow area of the cascade channels through air film holes arranged near the root of the cascade pressure surface. Because the air film holes are provided with proper compound angles and surface angles, the cooling air flow is injected into the blade grid channels from the junction of the horseshoe vortex and the angle vortex, and can be closely clung to the end wall to develop downstream under the entrainment action of the horseshoe vortex and the angle vortex. Therefore, on the premise of not increasing the blade cascade aerodynamic loss, the structure can be used for obviously improving the air film cooling efficiency of the end wall of the turbine near the pressure surface side and reducing the heat load of the end wall.

Description

Active wind shadow air film cooling structure for improving end wall cooling performance
Technical Field
The invention belongs to the technical field of turbines, relates to a gas film cooling structure, and in particular relates to an active wind shadow gas film cooling structure capable of improving cooling performance of an end wall.
Background
To improve gas turbine performance, high pressure turbine inlet temperatures are increasing and far exceeding metal creep temperatures. Furthermore, lean premixed combustors have been applied to gas turbines in recent years to improve engine compactness and reduce NOx emissions. Both of these aspects force the turbine first stage vane endwall region to operate in high temperature, high pressure, and complex flow environments. Therefore, an effective cooling technology must be applied to protect the turbine guide vane end wall from high temperature corrosion and damage to affect the operation safety of the whole machine.
In order to reduce the heat load of the end wall area, the air film cooling mode currently applied mainly comprises discrete air film hole cooling, blade grid channel gap cooling and blade grid upstream slot cooling. However, it is difficult to obtain an efficient cooling coverage of the cascade pressure side end wall using conventional cooling means. Studies have shown that the main flow of high temperature gas from upstream stagnates at the leading edge of the first stage vane and forms horseshoe vortices at the cascade root. The horseshoe vortex is divided into a left branch and a right branch at a stagnation point and enters the cascade channel to develop downstream. The water chestnut vortex pressure surface side branch is expanded to the suction surface side under the influence of transverse pressure gradient in the cascade channel, and the entrainment cooling gas leaves the wall surface and cannot reach the cascade pressure surface side end wall area, so that the cascade pressure surface side end wall air film cooling efficiency is seriously influenced. At the same time, the strong swirl characteristics of the lean premixed combustor outlet migrate downstream, directly affecting the aero-thermal characteristics of the first stage turbine. Related studies indicate that under swirl inlet conditions, horseshoe vortices are further enhanced, endwall thermal loading is further deteriorated and endwall gas film effectiveness is significantly reduced. In the case of long-term horseshoe vortex pressure face branch flushing without efficient film cooling coverage, the cascade pressure face side end wall is extremely susceptible to high temperature ablation and severely affects the safe operation and aerodynamic efficiency of the gas turbine.
Therefore, a novel efficient cooling structure is developed to protect the side end wall area of the cascade pressure surface from being ablated by main flow high-temperature air flow, the heat load of the area is reduced, and the safe and stable operation of the end wall area of the first-stage stationary blade is ensured, so that the novel efficient cooling structure has very important engineering application value.
Disclosure of Invention
Aiming at the problems that the turbine cascade end wall bears extremely high heat load and the cooling of the end wall area at the pressure surface side of the first-stage stationary blade is insufficient in a traditional cooling mode, the invention aims to provide an active wind shadow air film cooling structure for improving the cooling performance of the end wall. The invention can fundamentally reduce the heat load of the side end wall of the pressure surface of the blade cascade, ensure the safe and effective work of the end wall of the blade cascade and prolong the service life of the gas turbine.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows:
the active wind shadow air film cooling structure comprises an active wind shadow cooling cavity and a plurality of active wind shadow cooling air film holes, wherein the active wind shadow cooling cavity is arranged in a first-stage stationary blade of a turbine; the active wind shadow cooling air film hole is formed on the pressure surface side of the first-stage stationary blade, the active wind shadow cooling cavity is communicated with the blade grid channel through a certain jet angle, and during operation, cooling air flow is introduced from the bottom of the active wind shadow cooling cavity, enters a main flow area of the blade grid channel from the junction of the horseshoe vortex and the angle vortex through the active wind shadow cooling air film hole, and is developed towards the downstream by clinging to the end wall under the entrainment effect of the horseshoe vortex and the angle vortex, wherein the horseshoe vortex and the angle vortex are vortex formed by the gas main flow at the front edge stagnation of the first-stage stationary blade of the turbine and at the near end wall.
In one embodiment, the active wind shadow cooling plenum is located near the bottom of the first stage vane and extends through the root of the first stage vane in the flow direction.
In one embodiment, the active wind shadow cooling air film holes are arranged near the side root part of the pressure surface of the static blade and are formed along a certain jet angle.
In one embodiment, the distance l=0.1c of the active wind shadow cooling chamber from the vane leading edge in the axial direction of the blade ax Wherein C ax Is the axial chord length of the stator blade.
In one embodiment, the number of the active wind shadow cooling air film holes is 2-4, the sections of the air film holes are all round, the value range of the diameter d of each air film hole is 1-2mm, and the distance between adjacent air film holes is 4d.
In one embodiment, the active wind shadow cooling chamber is rectangular, the height a of the active wind shadow cooling chamber is 20d-30d, the width b of the active wind shadow cooling chamber is 3d-5d, the length c of the active wind shadow cooling chamber is 10d-15d, and the wall surface distance between the bottom of the active wind shadow cooling chamber and the end wall is 8d; wherein, the height refers to the height direction of the first-stage stationary blade; width refers to the circumferential direction of the blade; the length refers to the axial direction of the blade, and the bottom refers to the lower surface of the active wind shadow cooling cavity.
In one embodiment, the value range of the wall surface distance h between the outlet of the active wind shadow cooling air film hole and the end wall is 1%H-10% H, and H is the height of the stationary blade.
In one embodiment, the angle formed by the outflow direction of the active wind shadow cooling air film hole and the axial direction of the turbine is defined as a compound angle alpha, the angle formed by the outflow direction and the pressure surface of the static blade is defined as a surface angle beta, the value range of alpha is 10-30 degrees, and the value range of beta is 15-45 degrees.
In one embodiment, the outlets of the active wind shadow cooling film holes are at the junction of horseshoe vortices and angular vortices formed by the main flow of gas at the leading edge of the turbine first stage vane and at the proximal wall.
The invention also provides a turbine, which adopts the active wind shadow film cooling structure for improving the cooling performance of the end wall.
Compared with the prior art, the invention has the beneficial effects that:
the invention provides an active wind shadow air film cooling structure which can effectively improve the air film cooling efficiency of the side end wall of the turbine stator blade close to the pressure surface. The technical characteristics are that a plurality of air film cooling holes are arranged at the blade root of the near front edge on the pressure surface of the turbine stationary blade. The cooling air flow introduced from the air compressor passes through the wind shadow cooling chamber and then enters the blade grid channels from the air film hole outlets. Because the air film holes have proper surface angles and compound angles, one part of cooling gas moves along the root of the pressure surface along with the corner vortex, and the other part of cooling gas is wrapped by the horseshoe vortex and is tightly clung to the end wall to face the center of the channel to develop. Therefore, the cooling mode not only can cover the cascade pressure surface, but also can form secondary cooling in the cooling dead zone of the end wall near the pressure surface, so that the air film effectiveness of the end wall is greatly improved, and the problem that cooling gas cannot cover the end wall at the side of the pressure surface is solved.
1. The active wind shadow air film cooling structure designed by utilizing the flow characteristics of the horseshoe vortex and the angle vortex ensures that cooling gas can smoothly reach the end wall surface of the stationary blade to form cooling coverage. Therefore, on the premise of almost not causing the pneumatic loss of the blade cascade, the air film effectiveness of the end wall near the pressure surface side can be greatly improved by using less cooling gas, the loss of cold air is greatly avoided, and the working efficiency of the whole machine is improved.
2. Through preliminary verification of numerical simulation, even under the influence of strong swirl at an outlet of a real lean oil premixed combustion chamber, the film cooling structure still has good robustness, and the average film effectiveness of the end wall surface can be improved by about 50% only by using cooling gas with mass flow ratio mfr=0.5%. Therefore, in actual working conditions, the structure has good working performance and wide application prospect.
Drawings
FIG. 1 is a radial cross-sectional view of a typical conventional lean premixed combustor and a first stage turbine blade.
FIG. 2 is a schematic diagram of a turbine first stage vane and conventional endwall film cooling layout.
FIG. 3 is a first-stage meridian plane sectional view of a turbine with an active wind shadow film cooling structure.
FIG. 4 is a schematic illustration of a turbine first stage vane film cooling layout with active wind shadow film cooling.
FIG. 5 is a three-dimensional flow schematic of an active wind shadow film cooling jet and a typical endwall secondary flow.
FIG. 6 is an axial cross-sectional schematic view of an active wind shadow film cooling jet cooling regime.
FIG. 7 is a diagram of an active wind film cooling architecture according to the present invention.
FIG. 8 is a schematic view of a meridional view of a turbine vane with active wind shadow film cooling structure.
FIG. 9 is a top view of a turbine vane having an active wind film cooling structure.
Fig. 10 is a cloud chart of the end wall film effectiveness distribution with an active wind film cooling structure, wherein (a) is a conventional active wind film cooling structure without active wind film, (b) is example 1, (c) is example 2, and (d) is example 3.
FIG. 11 is an end wall circumferential average film effectiveness profile with an active wind film cooling structure.
Reference numerals illustrate:
1-a cooling structure of the inner wall of the combustion chamber; 2-combustion chamber; 3-a combustion chamber divergent cooling structure; 4-first stage vanes; 5-first stage moving blades; 6-a gas film cooling structure in the first-stage stationary blade channel; 7-a first-stage stationary blade upstream air film cooling structure; 8-a combustor swirl generator; 9-end walls; 10-active wind shadow cooling chamber; 11-active wind shadow cooling air film holes; 12-first stage vane leading edge; 13—first stage vane trailing edge.
Detailed Description
The invention is described in further detail below with reference to the drawings and the technical principles.
The conventional combustor, the first-stage turbine stator blade and the auxiliary air film cooling structure thereof are shown in fig. 1 and 2, and the first-stage turbine stator blade with the active air film cooling structure is shown in fig. 3 and 4. The design idea of the active wind shadow air film cooling structure is shown in fig. 5 and 6, and specific structural parameters and mounting positions are shown in fig. 7-9. Film cooling effect of the examples see fig. 10 and 11.
Referring to fig. 1 and 2, a swirl generator 8 is generally employed in a typical lean premixed combustor to ensure adequate and stable combustion of the fuel and air premixes. In addition, a low-temperature cooling air flow is emitted from the combustion chamber inner wall cooling structure 1 and the combustion chamber divergent cooling structure 3 for protecting the inner wall of the combustion chamber 2. Therefore, the downstream development of the main flow of gas is often accompanied by strong swirling and uneven temperature distribution characteristics, directly affecting the secondary flow development of the turbine first stage vanes 4 and first stage blades 5, and severely damaging the cooling protection of the endwalls 9 of the turbine first stage vanes. Traditional air film cooling structure design includes air film cooling structure 6 in the quiet leaf passageway of first order and the quiet leaf upper reaches air film cooling structure 7 of first order, all can not obtain better endwall air film cooling and cover. Referring to fig. 10, the numerical simulation results show that when the conventional film cooling structure is used, the end wall region has a large range without cooling protection, and the cooling air flow hardly reaches the side of the end wall 9 near the pressure surface. Therefore, in order to improve the effectiveness of the air film of the end wall 9 at the side of the near pressure surface and ensure the safe and stable operation of the engine, the invention is designed by using the following technical route:
referring to fig. 3 and 4, the active wind shadow air film cooling structure with the effect of improving the air film cooling effectiveness of the side end wall of the turbine first-stage stationary blade near the pressure surface provided by the invention comprises an active wind shadow cooling cavity 10 and a plurality of active wind shadow cooling air film holes 11. The active wind shadow cooling plenum 10 is disposed inside the first stage vane 4 of the turbine, and more specifically may be located near the bottom of the first stage vane 4 and extend through the root of the first stage vane 4 in the direction of flow of the cooling jet. The active wind shadow cooling film hole 11 is formed on the pressure surface side of the first stage stationary blade 4, more specifically, can be positioned at the blade root of the stationary blade pressure surface, and is formed along a certain jet angle, that is, the active wind shadow cooling cavity 10 is communicated with the blade cascade channel at a certain jet angle.
In the embodiment of the invention, the active wind shadow cooling air film hole 11 adopts the traditional air film hole with a circular cross section, the value range of the diameter d is 1-2mm, the distance between adjacent air film holes is 4d, the distance between the outlet of the active wind shadow cooling air film hole 11 and the wall surface of the end wall 9, namely the height of the air film hole outlet is H, which is determined according to the design of the static blade height H, generally, the value range of H is 1%H-10% H, the air film cooling effect of the end wall is reduced due to the fact that the H is not too large or too small, and the heat exchange coefficient of the local area of the end wall is too large due to the fact that the air film cooling effect of the end wall is too small. The distance L between the active wind shadow cooling chamber 10 and the front edge of the stator blade in the axial direction of the blade is 0.1C ax The near-pressure-face side end wall cooling coverage is very poor at this location, where C ax For vane axial chord length, each film hole has a compound angle α and a surface angle β depending on the particular blade design. Defining a compound angle alpha as an angle formed by the outflow direction of the active wind shadow cooling air film hole 11 and the axial direction of the turbine, and defining a surface angle beta as an angle formed by the outflow direction of the active wind shadow cooling air film hole 11 and the pressure surface of the stationary blade. The value range of alpha is 10-30 degrees, and the value range of beta is 15-45 degrees. Too large or too small a and β can result in a reduced end wall cooling footprint, reducing the wind shadow cooling gain effect. The number of the active wind shadow cooling air film holes 11 is properly increased and decreased according to the cooling effect, the range of the value is 2-4, the gain effect of the too small wind shadow cooling is not obvious, and the too large wind shadow cooling can cause the waste of cooling gas.
More specifically, in the embodiment of the present invention, the active wind shadow cooling chamber 10 is individually processed, mounted from the bottom of the first stage stator blade 4 to the inside of the blade, and is connected with the active wind shadow cooling film holes 11 processed on the blade to form a complete flow channel. The size of the active wind shadow cooling chamber 10 is not too small to be designed according to the blade geometry, and it is necessary to ensure that the cooling gas can be introduced from its bottom and uniformly pass through the active wind shadow cooling chamber 10 into the cascade channels. The active wind shadow cooling chamber 10 may be rectangular in shape, with a recommended size: the range of the height a is 20d-30d, the range of the width b is 3d-5d, and the range of the length c is 10d-15d. The distance between the bottom of the active wind shadow cooling chamber 10 and the wall surface of the end wall 9 is 8d so as to ensure that the cooling air flow can fully develop after being introduced from the bottom. In the present invention, the height is defined herein as the height direction along the first stage vane 4 blade; the width is along the circumferential direction of the blade; the length is along the axial direction of the blade, and the bottom is the lower surface of the active wind shadow cooling cavity 10.
The technical principle of the invention is seen in fig. 5 and 6, the main flow of gas is stopped at the leading edge 12 of the first stage vane of the turbine and forms vortices at the proximal wall 9, i.e. horseshoe vortices and angular vortices. The horseshoe vortex and the corner vortex develop downstream along the pressure and suction sides of the first stage vane 4 forming pressure side branches and suction side branches. The horseshoe vortex pressure side branch draws in near-endwall air flow exiting the endwall downstream of the cascade channels, so that conventional endwall film cooling air flow cannot enter the horseshoe vortex and corner vortex control regions. In use of the present invention, cooling air flow is introduced from the bottom of the active wind shadow cooling chamber 10, through the active wind shadow cooling film holes 11 and into the cascade channels. The height of the outlet of the active wind shadow cooling air film hole 11 is just at the junction of the horseshoe vortex and the angular vortex, and the air film hole has proper compound angle alpha and surface angle beta, so that cooling jet flows from the junction of the horseshoe vortex and the angular vortex into the main flow, enter the main flow area of the blade grid channel, and develop towards the downstream by the entrainment effect of the horseshoe vortex and the angular vortex, and cling to the end wall surface. Specifically, because the horseshoe vortex and the angular vortex have opposite rotational directions, the cooling jet is accelerated towards the end wall 9: on the one hand, the horseshoe vortex is led to flow to the end wall 9 in the channel (i.e. the cooling circuit 1 in the figure), and on the other hand, the horseshoe vortex is attracted to the joint between the stator blade and the end wall (i.e. the cooling circuit 2 in the figure). Therefore, the cooling structure can greatly improve the air film cooling effectiveness of the end wall of the turbine near the pressure surface side and reduce the heat load of the end wall on the premise of not increasing the air loss of the blade cascade.
The installation location and method of use of the present invention will be described in detail with reference to fig. 7-11 in conjunction with the following three embodiments and numerical simulation results. The first-stage stationary blade 4 and the traditional air film cooling structure aimed at by the three embodiments are completely the same, and only the distance h between the outlet of the active air film cooling air film hole and the end wall is changed.
The embodiment firstly depends on the axial chord length C of the first-stage stationary blade ax Defined as the distance in the axial direction between the first stage vane leading edge 12 and the first stage vane trailing edge 13, determines that the distance L between active wind shadow cooling and vane leading edge in the axial direction of the blade is 0.1C ax 。
The number of the adopted active wind shadow cooling air film holes 11 is 3, the diameter d of the air film holes is 1.5mm, and the distance between the adjacent air film holes is 6mm.
The height a of the active wind shadow cooling chamber 10 is 25d, which is 37.5mm. The width b of the active wind shadow cooling chamber is 4d, which is 6mm. The length c of the active wind shadow cooling chamber is 13d, which is 19.5mm. The wall spacing between the bottom of the active wind shadow cooling chamber 10 and the end wall 9 is 8d, which is 12mm.
After numerical simulation calculation, the migration paths of the horseshoe vortex and the angular vortex are mastered, and the optimal active wind shadow cooling air film hole composite angle alpha in the blade grid channel is determined to be 20 degrees, and the optimal active wind shadow cooling air film hole surface angle beta is determined to be 30 degrees.
On the basis of the determined parameters, three embodiments are respectively obtained by changing the ratio of the distance H between the outlet of the active wind shadow cooling air film hole and the end wall to the height H of the first-stage static blade: in the embodiment 1, the distance h between the outlet of the active wind shadow cooling air film hole and the end wall is 1.5 percent H, and the value is 2mm; in the embodiment 2, the distance h between the outlet of the active wind shadow cooling air film hole and the end wall is 4.0 percent H, and the value is 5mm; in example 3, the distance h between the outlet of the active wind shadow cooling air film hole and the end wall is 6.5% H, and the value is 8mm.
When the numerical simulation verifies the effectiveness of the design, the mass flow ratio MFR of the active wind shadow cooling jet flow to the main flow of the fuel gas is kept unchanged, and the value is 0.5%.
Fig. 10 and 11 show the comparison of the film cooling effectiveness of the three embodiments with the lower end wall 9 of the conventional film cooling structure. The effective coverage area of the air film under the traditional non-active air shadow cooling structure is smaller, the side end wall of the near pressure surface almost cannot obtain effective air film cooling protection, and the surface average air film cooling effectiveness is only 0.195. In the embodiment 1, the distance h between the outlet of the active wind shadow cooling air film hole and the end wall is smaller, more cooling gas is flushed into the blade grid channels along the cooling circuit 1, so that a higher air film cooling efficiency peak value is caused, the surface average air film cooling effectiveness is improved to 0.300%, and 53.8% is improved. In embodiment 3, the distance h between the outlet of the active wind shadow cooling air film hole and the end wall is larger, and the cooling air can develop to the downstream of the blade grating better, so that the air film cooling coverage in the blade grating channel is more uniform, the surface average air film cooling effectiveness is improved to 0.297, and the air film cooling effectiveness is improved by 52.3%.
In a word, the numerical simulation result shows that the method can obviously improve the effectiveness of the air film of the first-stage stator blade end wall of the turbine on the premise of not increasing the aerodynamic loss of the cascade channels, and obviously improve the cooling coverage of the side end wall of the near-pressure surface. The method has important significance for reducing the thermal load of the end wall of the first-stage stator blade of the turbine and ensuring the safe and stable operation of the engine. According to the active wind shadow air film cooling structure, a corresponding turbine can be obtained.

Claims (10)

1. The active wind shadow air film cooling structure for improving the end wall cooling performance is characterized by comprising an active wind shadow cooling cavity (10) and a plurality of active wind shadow cooling air film holes (11), wherein the active wind shadow cooling cavity (10) is arranged in a first-stage stationary blade (4) of a turbine; the active wind shadow cooling air film hole (11) is formed on the pressure surface side of the first-stage stationary blade (4), the active wind shadow cooling cavity (10) is communicated with the blade grid channel at a certain jet angle, during operation, cooling air flow is introduced from the bottom of the active wind shadow cooling cavity (10), enters a main flow area of the blade grid channel from the junction of the horseshoe vortex and the angle vortex through the active wind shadow cooling air film hole (11), and is developed towards the downstream by clinging to the end wall under the entrainment effect of the horseshoe vortex and the angle vortex, wherein the horseshoe vortex and the angle vortex are vortex formed by the fact that a gas main flow is stagnated at the front edge (12) of the first-stage stationary blade of the turbine and at the near end wall (9).
2. The active wind film cooling structure for improving endwall cooling performance according to claim 1, wherein the active wind film cooling chamber (10) is located near the bottom of the first stage vane (4) and penetrates the blade root of the first stage vane (4) in the flow direction.
3. The active wind shadow film cooling structure for improving end wall cooling performance according to claim 1, wherein the active wind shadow cooling film hole (11) is positioned near the side root part of the stationary blade pressure surface and is opened along a certain jet angle.
4. Active wind shadow film cooling structure for improving end wall cooling performance according to claim 1, characterized in that the distance l=0.1c between the active wind shadow cooling chamber (10) and the vane leading edge in the axial direction of the vane ax Wherein C ax Is the axial chord length of the stator blade.
5. The active wind shadow air film cooling structure for improving the end wall cooling performance according to claim 1, wherein the number of the active wind shadow cooling air film holes (11) is 2-4, the sections of the air film holes are all round, the value range of the diameter d of each air film hole is 1-2mm, and the distance between every two adjacent air film holes is 4d.
6. The active wind shadow film cooling structure for improving the cooling performance of the end wall according to claim 5, wherein the active wind shadow cooling cavity (10) is rectangular, the height a of the active wind shadow cooling cavity is 20d-30d, the width b of the active wind shadow cooling cavity is 3d-5d, the length c of the active wind shadow cooling cavity is 10d-15d, and the distance between the bottom of the active wind shadow cooling cavity (10) and the wall surface of the end wall (9) is 8d; wherein, the height refers to the blade height direction along the first-stage stationary blade (4); width refers to the circumferential direction of the blade; the length refers to the axial direction of the blade, and the bottom refers to the lower surface of the active wind shadow cooling cavity (10).
7. The active wind shadow film cooling structure for improving end wall cooling performance according to claim 5, wherein the value range of the wall surface distance h between the outlet of the active wind shadow cooling film hole (11) and the end wall (9) is 1%H-10% H, and H is the height of the stationary blade.
8. The active wind shadow film cooling structure for improving end wall cooling performance according to claim 5, wherein an angle formed between an outflow direction of the active wind shadow cooling film hole (11) and a turbine axial direction is defined as a compound angle alpha, an angle formed between the outflow direction and a stationary blade pressure surface is defined as a surface angle beta, the value of alpha is in the range of 10-30 degrees, and the value of beta is in the range of 15-45 degrees.
9. The active wind shadow film cooling structure for improving end wall cooling performance according to claim 5, wherein the outlet of the active wind shadow cooling film hole (11) is positioned at the junction of horseshoe vortex and angular vortex formed by the main flow of gas at the front edge (12) of the first stage stator blade of the turbine and at the near end wall (9).
10. Turbine employing the active wind shadow film cooling structure of any one of claims 1 to 9 for enhancing end wall cooling performance.
CN202310299167.1A 2023-03-24 2023-03-24 Active wind shadow air film cooling structure for improving end wall cooling performance Pending CN116085063A (en)

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Application Number Priority Date Filing Date Title
CN202310299167.1A CN116085063A (en) 2023-03-24 2023-03-24 Active wind shadow air film cooling structure for improving end wall cooling performance

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202310299167.1A CN116085063A (en) 2023-03-24 2023-03-24 Active wind shadow air film cooling structure for improving end wall cooling performance

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CN116085063A true CN116085063A (en) 2023-05-09

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