WO2019136672A1 - Plaque à rebord de pale de turbine basée sur une conception de courbe spline - Google Patents

Plaque à rebord de pale de turbine basée sur une conception de courbe spline Download PDF

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Publication number
WO2019136672A1
WO2019136672A1 PCT/CN2018/072280 CN2018072280W WO2019136672A1 WO 2019136672 A1 WO2019136672 A1 WO 2019136672A1 CN 2018072280 W CN2018072280 W CN 2018072280W WO 2019136672 A1 WO2019136672 A1 WO 2019136672A1
Authority
WO
WIPO (PCT)
Prior art keywords
edge plate
turbine blade
transition
plate body
edge
Prior art date
Application number
PCT/CN2018/072280
Other languages
English (en)
Chinese (zh)
Inventor
王志强
李立华
王俊
潘晓聪
Original Assignee
贵州智慧能源科技有限公司
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 贵州智慧能源科技有限公司 filed Critical 贵州智慧能源科技有限公司
Priority to PCT/CN2018/072280 priority Critical patent/WO2019136672A1/fr
Publication of WO2019136672A1 publication Critical patent/WO2019136672A1/fr

Links

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
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers

Definitions

  • the invention relates to a turbine blade edge plate, in particular to a turbine blade edge plate based on a spline curve design.
  • the high-temperature, high-speed, high-pressure fluid working from the combustion chamber expands continuously during the flow.
  • the fluid flow is very complicated, which is accompanied by the flow vortex and the secondary Energy loss phenomena such as flow.
  • the traditional turbine blade edge plates are mostly straight regular cuboids, such turbine blade edge plates will inevitably hinder the free expansion of the fluid working fluid, resulting in increased energy loss, and the transition between the first-stage turbine and the latter-stage turbine airflow. Not smooth and other issues.
  • the present invention proposes a turbine blade edge plate based on a spline curve design to effectively solve at least one of the problems set forth above.
  • the invention provides a turbine blade edge plate based on a spline design, comprising a flange body having an upper end surface and a lower end surface, the upper end surface being connected to the turbine blade, the lower end surface and a bottom end a toothed connection, the edge plate body has a curved structure as a whole, the edge plate body has a first end and a second end opposite to the first end, and the edge plate body is adjacent to the first end Arching up to form a raised portion, the raised portion having a rounded tip, the edge plate body being recessed downwardly adjacent the second end to form a lower recess, the lower recess having a wake Surface.
  • the turbine blade includes a blade surface and a blade root, and an upper end surface of the edge plate body is smoothly and transiently connected from a portion between the convex portion and the lower concave portion to the blade root portion.
  • the lower end surface of the edge plate body extends downward from the position of the convex portion to a first connecting portion, and the lower end surface of the edge plate body extends downward from the position of the lower concave portion to a second connecting portion.
  • the first connecting portion and the second connecting portion are for connecting with the molars.
  • a protrusion is formed between the protrusion and the first end, and the front extension and the first connection are connected by a circular arc, and the lower recess and the A rear extension portion is formed between the second ends, and the rear extension portion and the second connection portion are connected by a circular arc transition, and a flange transition portion is formed between the convex portion and the lower concave portion.
  • the upper end surface of the forward portion is a curved surface.
  • the forward portion is designed as a circular arc surface at a lower edge toward the first end
  • the rearward portion is designed as a circular arc surface at a lower edge toward the second end.
  • first connecting portion and the edge plate transition portion are connected by a circular arc
  • second connecting portion and the edge plate transition portion are connected by a circular arc
  • the thickness of the forward portion is greater than the thickness of the edge transition portion, and the thickness of the rear extension portion is greater than the thickness of the edge plate transition portion.
  • the edge plate transition portion is 17 degrees from the axial direction of the edge plate.
  • the arc curve of the lower edge arc surface of the front extension portion is 11 degrees
  • the arc curve of the lower edge arc surface of the rear extension portion is 11 degrees
  • the present invention proposes a turbine blade edge plate based on a spline curve, which solves the problem that the conventional turbine blade edge plate is a straight regular plane body, which causes an increase in energy loss due to the free expansion of the fluid working medium.
  • the turbine blade edge plate conforms to fluid aerodynamic performance, can improve turbine efficiency, and delay material fatigue failure.
  • the smooth transition between the edge plate and the blade root spline curve avoids the appearance and expansion of the flow path vortex and secondary flow, thereby improving efficiency.
  • the front and rear extensions of the edge plate body are designed with a sealing structure to prevent fluid working fluid from leaking from the radial gap, so that the fluid working medium can be used as much as possible for work and avoid high temperature fluid working fluid leakage, resulting in the entire rotor temperature field.
  • the imbalance affects material properties.
  • the curved body extending forward and backward of the edge plate can solve the problems that the transition of the first-stage turbine and the latter-stage turbine airflow is not smooth, and the blade root leaks.
  • FIG. 1 is a schematic view showing the combined structure of a turbine blade, a rim and a dent of the present invention.
  • FIG. 2 is a structural schematic view of a rounded transition of a blade root and a flange body of a turbine blade of the present invention.
  • FIG. 3 is a schematic structural view of a body of a rim of the present invention.
  • FIG. 4 is a partial perspective view of the body of the edge plate of the present invention.
  • the present invention proposes a turbine blade edge plate based on a spline curve design, the turbine blade edge plate having a curved structure as a whole.
  • the turbine blade rim includes a rim body 10, turbine blades 16 and teeth 18 on opposite sides of the rim body 10.
  • the edge plate body 10 has an upper end surface 12 and a lower end surface 14, wherein the upper end surface 12 is smoothly connected to the turbine blade 16, and the lower end surface 14 is connected to the molar tooth 18.
  • the edge plate body 10 has a first end 20 and a second end 22 opposite the first end 20.
  • the edge plate body 10 is upwardly arched at a position close to the first end 20 to form a convex portion 24, and in the present embodiment, both side edges of the convex portion 24 are rounded curved sides.
  • the raised portion 24 has a rounded tip 26.
  • the primary function of the circular tip 26 is to direct the airflow to work on the turbine blades 16.
  • the edge plate body 10 is recessed downward at a position close to the second end 22 to form a lower concave portion 28. In the present embodiment, both side edges of the lower concave portion 28 are rounded curved sides.
  • the recessed portion 28 has a wake surface 30, and the wake surface 30 functions primarily as a rectification.
  • the turbine blade 16 includes a blade surface 32 and a blade root 34.
  • the blade root 34 and the upper end surface 12 of the edge plate body 10 are smoothly transitioned from the portion between the boss 24 and the lower recess 28, so that the design is designed to smooth the airflow. Flowing through the blade root 34 reduces the generation of secondary flow and vortex.
  • the lower end surface 14 of the edge plate body 10 extends downward from the position of the convex portion 24 to a first connecting portion 36.
  • the lower end surface 14 of the edge plate body 10 extends downward from the position of the lower concave portion 28 to form a second connecting portion 38.
  • the first connecting portion 36 and the second connecting portion 38 are respectively connected to the molars 18, for example, integrally formed.
  • the convex portion 24 and the first end 20 of the edge plate body form a forward portion 40 of the edge plate body 10.
  • the upper end surface 42 of the front extension portion 40 is a curved surface, and its main function It is sealed and rectified so that the airflow at the blade root 34 can conform to the fluid flow downstream.
  • the front extension 40 and the first connection portion 36 are connected by a circular arc.
  • a rearward extending portion 44 of the edge plate body 10 is formed between the lower recessed portion 28 and the second end 22 of the edge plate body, and the rearward extending portion 44 and the second connecting portion 38 are connected by a circular arc.
  • a rim transition 46 is formed between the raised portion 24 and the lower recess 28, and the edge transition portion 46 is 17 degrees from the axial direction of the rim.
  • the edge plate transition portion 46 is designed to be 17 degrees from the axial direction of the edge plate so that the edge plate is optimal in the problem of smooth airflow, and the airflow rapidly expands as it passes over the edge plate surface and the blade surface 32. The presence of the sloped surface is in line with the airflow expansion characteristics.
  • the thickness of the forward portion 40 is greater than the thickness of the edge transition 46, and the thickness of the rearward portion 44 is greater than the thickness of the edge transition 46.
  • This design mainly considers the effects of centrifugal stress and airflow force, and it is necessary to increase the thickness to offset the stress concentration point.
  • the thinner transition of the rim transition 46 is primarily a consideration of the need to minimize weight on the basis of structural strength. Further, the thickness of the edge plate can be appropriately adjusted in accordance with the gas force of the turbine blade 16.
  • the first connecting portion 36 and the edge plate transition portion 46 are connected by a circular arc, and the second connecting portion 38 and the edge plate transition portion 46 are connected by a circular arc.
  • the main purpose of this design is to reduce stress concentration through a smooth transition.
  • the forwardly extending portion 40 is designed as a circular arc surface at a lower edge facing the first end 20 of the edge plate body
  • the rearward extending portion 44 is designed as a circular arc surface at a lower edge of the second end 22 of the edge plate body.
  • the arc curve of the lower edge arc surface of the front extension portion 40 is designed to be 11 degrees
  • the arc curve of the lower edge arc surface of the rear extension portion 44 is designed to be 11 degrees
  • the angle design is matched with The turbine disk fits snugly and, in addition, achieves uniform stress.
  • the first end 20 serves as the front end of the edge plate body 10, and can be adjusted in accordance with the actual force of the turbine blade 16; the length of the lower surface of the first connecting portion 36 can match the change of the frequency of the turbine blade 16.
  • the adjustment; the length of the lower surface of the front extension 40 can be adjusted in accordance with the rectification and sealing action of the curved surface of the front extension 40.
  • the present invention proposes a turbine blade edge plate based on a spline curve, which solves the problem that the conventional turbine blade edge plate is a straight regular plane body, which causes an increase in energy loss due to the free expansion of the fluid working medium.
  • the turbine blade edge plate conforms to fluid aerodynamic performance, can improve turbine efficiency, and delay material fatigue failure.
  • the smooth transition between the edge plate and the blade root spline curve avoids the appearance and expansion of the flow path vortex and secondary flow, thereby improving efficiency.
  • the front and rear extensions of the edge plate body are designed with a sealing structure to prevent fluid working fluid from leaking from the radial gap, so that the fluid working medium can be used as much as possible for work and avoid high temperature fluid working fluid leakage, resulting in the entire rotor temperature field.
  • the imbalance affects material properties.
  • the curved body extending forward and backward of the edge plate can solve the problems that the transition of the first-stage turbine and the latter-stage turbine airflow is not smooth, and the blade root leaks.

Landscapes

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

Abstract

La présente invention concerne une plaque à rebord de pale de turbine basée sur une conception de courbe spline, comprenant un corps de plaque à rebord (10) ayant une face d'extrémité supérieure (12) et une face d'extrémité inférieure (14), la face d'extrémité supérieure étant raccordée à une pale de turbine (16) et la face d'extrémité inférieure étant raccordée à des dents de tenon (18). Le corps de plaque à rebord présente une structure globalement en forme de courbe et possède une première extrémité (20) et une seconde extrémité (22) opposées l'une à l'autre. Le corps de plaque à rebord est incurvé vers le haut au niveau d'un emplacement adjacent à sa première extrémité pour former une partie en saillie (24) et est évidé vers le bas au niveau d'un emplacement adjacent à la seconde extrémité pour former une partie évidée (28). La partie en saillie présente une pointe circulaire (26) et la partie évidée a une surface incurvée d'écoulement de sillage (30).
PCT/CN2018/072280 2018-01-11 2018-01-11 Plaque à rebord de pale de turbine basée sur une conception de courbe spline WO2019136672A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/CN2018/072280 WO2019136672A1 (fr) 2018-01-11 2018-01-11 Plaque à rebord de pale de turbine basée sur une conception de courbe spline

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2018/072280 WO2019136672A1 (fr) 2018-01-11 2018-01-11 Plaque à rebord de pale de turbine basée sur une conception de courbe spline

Publications (1)

Publication Number Publication Date
WO2019136672A1 true WO2019136672A1 (fr) 2019-07-18

Family

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PCT/CN2018/072280 WO2019136672A1 (fr) 2018-01-11 2018-01-11 Plaque à rebord de pale de turbine basée sur une conception de courbe spline

Country Status (1)

Country Link
WO (1) WO2019136672A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114075997A (zh) * 2020-08-20 2022-02-22 曹建礼 一种异形蜗轮叶片

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050186074A1 (en) * 2004-02-23 2005-08-25 Mitsubishi Heavy Industries, Ltd. Moving blade and gas turbine using the same
CN1908379A (zh) * 2005-08-03 2007-02-07 联合工艺公司 低支壁应力的涡轮翼面平台的鸭嘴兽形结构
CN102953764A (zh) * 2011-08-23 2013-03-06 通用电气公司 连接的叶片平台以及密封方法
CN204419273U (zh) * 2015-01-06 2015-06-24 中国航空工业集团公司沈阳发动机设计研究所 一种涡轮转子叶片定位结构
CN206448844U (zh) * 2017-02-22 2017-08-29 成都成发科能动力工程有限公司 一种透平机转子动叶片及透平机转子动叶片安装结构

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050186074A1 (en) * 2004-02-23 2005-08-25 Mitsubishi Heavy Industries, Ltd. Moving blade and gas turbine using the same
CN1908379A (zh) * 2005-08-03 2007-02-07 联合工艺公司 低支壁应力的涡轮翼面平台的鸭嘴兽形结构
CN102953764A (zh) * 2011-08-23 2013-03-06 通用电气公司 连接的叶片平台以及密封方法
CN204419273U (zh) * 2015-01-06 2015-06-24 中国航空工业集团公司沈阳发动机设计研究所 一种涡轮转子叶片定位结构
CN206448844U (zh) * 2017-02-22 2017-08-29 成都成发科能动力工程有限公司 一种透平机转子动叶片及透平机转子动叶片安装结构

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114075997A (zh) * 2020-08-20 2022-02-22 曹建礼 一种异形蜗轮叶片
CN114075997B (zh) * 2020-08-20 2024-05-31 曹建礼 一种异形涡轮叶片

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