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CN115059518B - Air-cooled turbine guide vane trailing edge structure of suction side exhaust - Google Patents

Air-cooled turbine guide vane trailing edge structure of suction side exhaust Download PDF

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Publication number
CN115059518B
CN115059518B CN202210595200.0A CN202210595200A CN115059518B CN 115059518 B CN115059518 B CN 115059518B CN 202210595200 A CN202210595200 A CN 202210595200A CN 115059518 B CN115059518 B CN 115059518B
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exhaust
tail edge
turbine
guide vane
edge
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CN115059518A (en
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牛夕莹
孙鹏
林枫
李宗全
李国强
李翔宇
毛冬岩
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703th Research Institute of CSIC
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703th Research Institute of CSIC
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00Stators
    • F01D9/02Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08Cooling; Heating; Heat-insulation
    • F01D25/12Cooling

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention provides an air-cooled turbine guide vane trailing edge structure of suction side exhaust, which is a trailing edge structure for discharging cooling air through the suction side of the turbine guide vane trailing edge. The invention aims to provide a tail edge exhaust structure which can effectively reduce the thickness of the tail edge of a turbine guide vane, reduce the wake loss of the turbine guide vane, improve the aerodynamic performance of a turbine blade, reduce the exhaust pressure of cooling air, increase the exhaust speed, improve the cooling effect of the tail edge, reduce the temperature of the tail edge and prolong the service life of the blade. Therefore, the difficult problem of large loss of the guide vane wake in the traditional tail edge middle split joint exhaust mode is solved. The invention is used for improving the loss of the turbine guide vane wake of the gas turbine and reducing the temperature of the turbine guide vane tail edge.

Description

Air-cooled turbine guide vane trailing edge structure of suction side exhaust
Technical Field
The invention relates to an air-cooled turbine guide vane trailing edge structure of suction side exhaust, in particular to a trailing edge structure which can effectively reduce turbine guide vane wake loss and improve aerodynamic performance of turbine guide vanes by discharging cooling air through the suction side of the turbine guide vane trailing edge.
Background
The gas turbine has the advantages of high power density, high starting speed, flexible fuel and the like, is widely applied to the fields of power generation of industrial and offshore platforms, natural gas transportation, petrochemical industry, metallurgy and the like, and can also be used as a main power device of an airplane, a ship and a ground vehicle.
Modern high performance gas turbines are continually increasing in gas initial temperature (turbine inlet temperature) for higher cycle efficiency, higher power. With the increasing temperature of the turbine inlet, the operating temperature of the turbine is far above the melting point temperature of the blade materials, such as the turbine inlet gas temperature of the most advanced gas turbine which is put into operation at present reaches 1600 ℃, and the turbine inlet temperature of the advanced aero-engine is more than 1800 ℃. There are three main measures to ensure that a gas turbine blade can safely and reliably operate for a long period of time in such a high temperature environment: firstly, the heat-resistant grade of the turbine blade material is continuously improved, secondly, an advanced cooling technology is adopted to reduce the temperature of the blade, and thirdly, the heat-insulating effect of the heat-insulating coating of the turbine blade is continuously improved. In recent years, the increase in turbine inlet temperature has been mainly due to the increase in turbine cooling design level, and secondly due to the development of high-performance heat-resistant alloys and coating materials and the progress of the production and manufacturing process level. Obviously, turbine blade cooling plays a vital role in increasing turbine inlet temperature and improving gas turbine performance.
In recent years, with the continuous progress of design technology and the continuous development of computational fluid mechanics, the full three-dimensional optimization design means are continuously applied in the process of turbine cooling design, the turbine cooling design system, design means and method are continuously abundant and perfect, the advanced design technology and cooling structure continuously promote the improvement of turbine inlet temperature, and the shape of a turbine blade cooling channel is also more complex. In order to meet the requirements of energy conservation and emission reduction, the modern gas turbine is continuously pursued for performance improvement, turbine cooling and pneumatic performance are required to be continuously improved, and the service life and reliability of turbine blades are continuously improved. However, cooling techniques based on conventional turbine blade trailing edge exhaust structures have difficulty in improving turbine blade aerodynamics while reducing blade trailing edge temperature.
Although scholars and scientific researchers at home and abroad have conducted a great deal of research on the aspects of efficient cooling and aerodynamic design of turbine blades and have certain knowledge on improving the cooling and aerodynamic performance of the turbine blades and revealing the internal cooling flow mechanism of the turbine blade bodies, the research does not pay attention to how to improve the blade profile loss of the turbine blades while improving the cooling of the turbine blade bodies, and reports on the aspects of reducing the metal temperature of the tail edges of the turbine blades and improving the aerodynamic performance of turbine blades through the exhaust structure form of the suction side of the tail edges of the guide vanes are also fresh. Scientific researchers hope to have an advanced trailing edge structural form which can solve the problem that the trailing edge of the turbine guide vane is difficult to cool and can effectively improve the pneumatic performance of the turbine guide vane.
Disclosure of Invention
The invention aims to provide a tail edge exhaust structure which can effectively reduce the thickness of the tail edge of a turbine guide vane, reduce the wake loss of the turbine guide vane, improve the aerodynamic performance of a turbine blade, reduce the exhaust pressure of cooling air, increase the exhaust speed, improve the cooling effect of the tail edge, reduce the temperature of the tail edge and prolong the service life of the blade. Therefore, the difficult problem of large loss of the guide vane wake in the traditional tail edge middle split joint exhaust mode is solved.
The purpose of the invention is realized in the following way: the cooling air exhaust system comprises a long exhaust tail edge, a short exhaust tail edge, exhaust connecting ribs and exhaust gratings, wherein a cooling air exhaust channel with an open single side is formed between the long exhaust tail edge and the short exhaust tail edge, the cooling air exhaust channel with the open single side is divided into the exhaust gratings along the exhaust connecting ribs uniformly distributed in the height direction of the blade, the final turbine guide blade tail edge cooling air exhaust channel is further formed, and cooling air in the turbine guide blade is discharged into the blade grating channel after the tail edge of the turbine guide blade is cooled by the exhaust gratings. The air-cooled turbine vane trailing edge structure exhaust grille 5 of the suction side exhaust is arranged on the back side of the turbine vane blades.
Further, the long exhaust tail edge, the short exhaust tail edge and the exhaust connecting ribs are sequentially connected into a whole.
Further, the long exhaust tail edge is obtained along the line of the suction surface of the guide vane blade.
Further, the long exhaust trailing edge and the short exhaust trailing edge extend to a length of less than 5mm on the back side of the blade.
Further, the included angle (a) between the long and short exhaust trailing edges is within 8 degrees.
Further, the trailing edge radius of the long exhaust trailing edge is 0.4mm.
Further, the tail edge radius of the short exhaust tail edge is 0.3mm.
Compared with the prior art, the invention has the beneficial effects that: compared with the traditional exhaust structure form of the split joint in the middle of the tail edge of the turbine guide vane, the suction side exhaust structure of the invention can reduce the thickness of the tail edge of the turbine guide vane, thereby reducing the vane profile loss of the turbine guide vane, improving the aerodynamic performance of the turbine guide vane, improving the efficiency of the turbine and the whole machine set and reducing the energy consumption, and solving the problems that the tail loss of the movable vane is large and the aerodynamic efficiency of the turbine is difficult to meet the requirement in the traditional exhaust mode of the split joint in the middle of the tail edge.
By adopting the turbine guide vane, compared with a middle split joint tail edge exhaust structure on the premise that the tail edge of the guide vane has the same cooling air flow, the wake loss is reduced by 50% under the condition that the temperature of the tail edge of the guide vane is unchanged.
Drawings
FIG. 1 is a schematic view of a turbine vane trailing edge exhaust structure of the present invention;
FIG. 2 is a schematic cross-sectional view of a turbine vane trailing edge exhaust structure of the present invention;
FIG. 3 is a schematic view of a turbine cascade channel with the turbine vane trailing edge exhaust structure of the present invention;
FIG. 4 is a schematic view of the dimensions and angles of the turbine vane trailing edge exhaust structure of the present invention;
fig. 5 is a schematic diagram of a conventional turbine vane trailing edge intermediate split exhaust structure.
Detailed Description
The invention is described in further detail below with reference to the drawings and the detailed description.
The first embodiment is as follows: referring to fig. 1 to 3, a suction side exhaust gas air-cooled turbine vane trailing edge structure according to the present embodiment is described, and includes a long exhaust trailing edge 1, a short exhaust trailing edge 2, and an exhaust connecting rib 3, wherein a cooling air exhaust passage 4 with one open side is formed between the long exhaust trailing edge 1 and the short exhaust trailing edge 2, the cooling air exhaust passage 4 with one open side is divided into individual exhaust gratings 5 by the exhaust connecting rib 3 uniformly distributed along the blade height direction, and then a final turbine vane trailing edge cooling air exhaust passage 6 is formed, and cooling air inside the turbine vane is discharged from the individual exhaust gratings 5 of the trailing edge, and the cooling vane short exhaust trailing edge 2, the exhaust connecting rib 3, and the long exhaust trailing edge 1 are discharged into the vane grating passage.
The second embodiment is as follows: the long exhaust tail edge 1, the short exhaust tail edge 2, and the exhaust connecting rib 3 according to the present embodiment are sequentially connected to each other as a unit, which will be described with reference to fig. 1. By the arrangement, compared with a conventional turbine guide vane trailing edge structure, the connection between the long exhaust trailing edge 1 and the short exhaust trailing edge 2 of the guide vane can be enhanced, an integrated structure is formed, the stress state of the turbine guide vane trailing edge is improved, the strength of the turbine guide vane is enhanced, and the reliability and the service life of the turbine guide vane are improved.
Other compositions and connection relationships are the same as those of the first embodiment.
And a third specific embodiment: the present embodiment is described with reference to fig. 2 to 4, in which the long exhaust trailing edge 1 is obtained along the guide vane suction surface profile 7. By the arrangement, on one hand, flow disorder caused by steps can be reduced, flow loss of the blade profile is increased, on the other hand, improvement of a wave system structure of the tail edge accessory is facilitated, shock wave loss is reduced, and accordingly the blade profile and the flow loss are comprehensively reduced.
Other compositions and connection relationships are the same as those of the first or second embodiment.
The specific embodiment IV is as follows: the present embodiment will be described with reference to fig. 2 to 4, in which the long exhaust trailing edge 1 and the short exhaust trailing edge 2 of the present embodiment extend within 5mm on the back side. Compared with the traditional turbine guide vane trailing edge pressure side exhaust structure, the suction side exhaust structure can reduce turbine cooling air exhaust pressure and increase exhaust speed, on one hand, the effect of convection heat exchange of the trailing edge cooling air can be improved, on the other hand, the length of the long exhaust trailing edge 1, the short exhaust trailing edge 2 extending out of the vane back side is smaller, so that the heated area can be reduced, the metal temperature near the turbine guide vane trailing edge is comprehensively reduced, and the service life of the turbine guide vane is prolonged; compared with the traditional exhaust structure form of the split joint in the middle of the tail edge of the turbine guide vane, the suction side exhaust can reduce the thickness of the tail edge of the turbine guide vane, thereby reducing the vane profile loss of the turbine guide vane, improving the aerodynamic performance of the turbine guide vane, improving the efficiency of the turbine and the whole machine unit and reducing the energy consumption.
Other compositions and connection relationships are the same as those of the first, second or third embodiments.
Fifth embodiment: the present embodiment will be described with reference to fig. 2 to 4, in which the angle (a) between the long exhaust trailing edge 1 and the short exhaust trailing edge 2 is 8 degrees or less. By the arrangement, smooth transition between the short exhaust tail edge 2 and the long exhaust tail edge 1 can be realized, larger wake loss caused by steps after the short exhaust tail edge 2 due to overlarge angles is avoided, the thickness of the long exhaust tail edge 1 is reduced, compared with the traditional turbine guide vane tail edge middle split joint exhaust structure, the turbine guide vane blade profile loss is reduced, and the aerodynamic performance of the turbine guide vane is improved.
Other compositions and connection relationships are the same as those of the first, second, third or fourth embodiments.
Specific embodiment six: the present embodiment will be described with reference to fig. 2 and 3, in which the long exhaust trailing edge 1 has a trailing edge radius of 0.4mm. Compared with the traditional turbine vane tail edge middle split joint exhaust structure vane profile, the radial of the vane tail edge is reduced, the ratio of the tail edge thickness to the chord length is reduced by more than 200%, the width of the vane tail trace is narrowed, on one hand, the vane profile flow loss is reduced, and the turbine aerodynamic efficiency is improved; on the other hand, the wake becomes narrow, the pressure fluctuation of the tail edge is smaller, the exciting force caused by the wake flowing is weakened, and the stress state of the downstream movable blade is improved.
Other compositions and connection relationships are the same as those of the first, second, third, fourth or fifth embodiments.
Seventh embodiment: the present embodiment will be described with reference to fig. 2 and 3, in which the tail radius of the short exhaust tail 2 is 0.3mm. By the arrangement, on one hand, loss of the blade wake near the short exhaust tail edge 2 is reduced, and on the other hand, smooth transition between the short exhaust tail edge 2 and the long exhaust tail edge 1 is facilitated, the extension length is shortened, the included angle (A) is reduced, and therefore aerodynamic performance of the turbine guide vane is improved.
Other compositions and connection relationships are the same as those of the first, second, third, fourth, fifth or sixth embodiments.
The working principle thereof is illustrated by fig. 1-4:
the cooling air exhaust system comprises a long exhaust tail edge 1, a short exhaust tail edge 2 and exhaust connecting ribs 3, wherein a cooling air exhaust channel 4 with an open single side is formed between the long exhaust tail edge 1 and the short exhaust tail edge 2, the cooling air exhaust channel 4 with the open single side is divided into exhaust grids 5 by the exhaust connecting ribs 3 which are uniformly distributed along the height direction of the blade, a final turbine guide vane tail edge cooling air exhaust channel 6 is formed, cooling air in the turbine guide vane is exhausted from the exhaust grids 5, and the cooling guide vane short exhaust tail edge 2, the exhaust connecting ribs 3 and the long exhaust tail edge 1 are discharged into the blade grid channel. After the air-cooled turbine guide vane trailing edge structure of suction side exhaust is adopted, on one hand, the connection between the long exhaust trailing edge 1 and the short exhaust trailing edge 2 of the guide vane is reinforced through the exhaust connecting ribs 3 to form an integrated structure, and the stress state of the turbine guide vane trailing edge is improved, so that the strength of the turbine guide vane is enhanced, and the reliability and the service life of the turbine guide vane are improved; on the other hand, compared with the traditional exhaust structure form of the split joint in the middle of the tail edge of the turbine guide vane, the suction side exhaust can reduce the thickness of the tail edge of the turbine guide vane, thereby reducing the vane profile loss of the turbine guide vane, improving the aerodynamic performance of the turbine guide vane, improving the efficiency of the turbine and the whole machine set, reducing the energy consumption and fundamentally solving the problem that the efficiency of the exhaust structure of the split joint in the middle of the tail edge of the traditional turbine guide vane is difficult to meet the requirement.
In summary, the present invention relates to a trailing edge structure of an air-cooled turbine vane for suction side exhaust, and more particularly, to a trailing edge structure for discharging cooling air through a suction side of a turbine vane trailing edge. The invention aims to provide a tail edge exhaust structure which can effectively reduce the thickness of the tail edge of a turbine guide vane, reduce the wake loss of the turbine guide vane, improve the aerodynamic performance of a turbine blade, reduce the exhaust pressure of cooling air, increase the exhaust speed, improve the cooling effect of the tail edge, reduce the temperature of the tail edge and prolong the service life of the blade. Therefore, the difficult problem of large loss of the guide vane wake in the traditional tail edge middle split joint exhaust mode is solved. The invention is used for improving the loss of the turbine guide vane wake of the gas turbine and reducing the temperature of the turbine guide vane tail edge.

Claims (2)

1. The utility model provides a cold turbine stator trailing edge structure of suction side exhaust which characterized in that: the cooling air exhaust system comprises a long exhaust tail edge, a short exhaust tail edge and exhaust connecting ribs, wherein a cooling air exhaust channel with an open single side is formed between the long exhaust tail edge and the short exhaust tail edge, the cooling air exhaust channel with the open single side is divided into exhaust grids by the exhaust connecting ribs uniformly distributed along the height direction of the blade, the exhaust grids are arranged on the blade basin side of the turbine guide blade, so that a final cooling air exhaust channel of the tail edge of the turbine guide blade is formed, cooling air in the turbine guide blade is exhausted from the exhaust grids, and is exhausted into the blade grid channel after passing through the short exhaust tail edge, the exhaust connecting ribs and the long exhaust tail edge of the cooling guide blade; the extension length of the short exhaust tail edge of the long exhaust tail edge on the side of the leaf basin is within 5 mm; the included angle between the long exhaust tail edge and the short exhaust tail edge is within 8 degrees; the tail edge radius of the long exhaust tail edge is 0.4mm; the tail edge radius of the short exhaust tail edge is 0.3mm, and the long exhaust tail edge is obtained along the contour of the pressure surface of the guide vane.
2. The suction side exhaust gas air cooled turbine vane trailing edge structure of claim 1, wherein: the long exhaust tail edge and the short exhaust tail edge are connected into a whole through an exhaust connecting rib.
CN202210595200.0A 2022-05-29 2022-05-29 Air-cooled turbine guide vane trailing edge structure of suction side exhaust Active CN115059518B (en)

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Citations (2)

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US8070441B1 (en) * 2007-07-20 2011-12-06 Florida Turbine Technologies, Inc. Turbine airfoil with trailing edge cooling channels
CN110925027A (en) * 2019-11-29 2020-03-27 大连理工大学 Turbine blade trailing edge tapered inclined exhaust split structure

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CN103270296B (en) * 2011-10-12 2014-05-07 三菱重工业株式会社 Wind turbine blade, wind power generation device provided with same, and design method for wind turbine blade
MX365406B (en) * 2013-07-30 2019-05-31 Lm Wp Patent Holding As A wind turbine blade having a bond line adjacent a sandwich panel of the blade.
CN103912316A (en) * 2014-04-11 2014-07-09 北京航空航天大学 Slotted air film cooling structure for guide blades of turbines
US20160160653A1 (en) * 2014-12-08 2016-06-09 Hyundai Motor Company Turbine wheel for turbo charger
US20210276077A1 (en) * 2018-07-18 2021-09-09 Poly6 Technologies, Inc. Articles and methods of manufacture
CN111102012B (en) * 2018-10-25 2024-07-09 中国科学院工程热物理研究所 Blade adopting self-adaptive coanda jet and manufacturing method
CN115126547B (en) * 2022-05-29 2023-05-12 中国船舶重工集团公司第七0三研究所 Air-cooled turbine movable blade trailing edge structure for suction side exhaust

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8070441B1 (en) * 2007-07-20 2011-12-06 Florida Turbine Technologies, Inc. Turbine airfoil with trailing edge cooling channels
CN110925027A (en) * 2019-11-29 2020-03-27 大连理工大学 Turbine blade trailing edge tapered inclined exhaust split structure

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