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A blade body structure of a turbine blade

A technology of turbine blades and blade profiles, which is applied in the directions of blade support elements, engine elements, machines/engines, etc., can solve the problem of not considering secondary flow loss, turbine blade airfoil profile loss, and failure to consider secondary flow. Loss and other issues, to achieve the effect of being beneficial to large-scale application and promotion, improving aerodynamic performance, and reducing lateral pressure gradient

Active Publication Date: 2017-07-28
DONGFANG TURBINE CO LTD
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Problems solved by technology

[0002] The airfoil shape of the existing turbine blades is mainly limited to the surface friction loss of the two-dimensional airfoil (the two-dimensional airfoil refers to the shape of the cross-sectional profile of the airfoil), that is, the profile loss, which is mainly considered It is the middle area of ​​the blade body of the turbine blade (that is, the main flow area), and does not consider the secondary flow loss
However, in the structure of the turbine blade, another main source of the loss of the turbine blade airfoil is the secondary flow loss in the airfoil end area (that is, the root area and the top area of ​​the turbine blade airfoil)
This turbine blade airfoil structure, which does not consider the secondary flow loss, has technical problems of low aerodynamic performance and high aerodynamic loss

Method used

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  • A blade body structure of a turbine blade
  • A blade body structure of a turbine blade
  • A blade body structure of a turbine blade

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Embodiment Construction

[0023] see figure 1 and figure 2 As shown, the present invention is an airfoil structure of a turbine blade. The airfoil of a turbine blade 1 is composed of a bottom-up root region 2, a middle region 3 and a top region 4, and each region has a matching two Dimensional airfoil 5, the two-dimensional airfoil refers to the shape of the cross-sectional profile of the airfoil.

[0024] The two-dimensional airfoil 5 of the blade body of the turbine blade 1 is a crescent-shaped closed curve surrounded by the inner arc curve and the back arc curve, which has a characteristic parameter chord length CH (the small circle on the inlet and outlet sides of the two-dimensional airfoil shape In the direction of the common tangent line, the maximum width of the two-dimensional airfoil), the axial width CX (the maximum width of the two-dimensional airfoil in the air inlet direction), the pitch T (the distance between adjacent two-dimensional airfoils), and the throat width TH (minimum channe...

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Abstract

The invention discloses a blade body structure of a turbine blade. The two-dimensional blade shape of the blade body is a crescent-shaped closed curve surrounded by an inner arc curve and a back arc curve, and has characteristic parameters of chord length CH and axial width CX. The airfoil is formed by twisting and superimposing several two-dimensional airfoils according to a certain rule, and has a characteristic parameter airfoil height H; the chord length CH of the two-dimensional airfoil forms a parabolic distribution law from the root to the top along the blade height direction, The trend is that the root and top chords of the blade body grow longer, and the middle chord length is smaller; the axial width CX of the two-dimensional airfoil remains basically unchanged. The invention can make the turbine blade take into account different main loss sources in the root area, the top area and the middle area at the same time, so as to effectively and reliably improve the aerodynamic performance of the turbine blade and reduce the aerodynamic loss.

Description

technical field [0001] The invention relates to a turbine blade, in particular to a blade body structure of a turbine blade. Background technique [0002] The airfoil shape of the existing turbine blades is mainly limited to the surface friction loss of the two-dimensional airfoil (the two-dimensional airfoil refers to the shape of the cross-sectional profile of the airfoil), that is, the profile loss, which is mainly considered It is the middle area of ​​turbine blade airfoil (that is, the main flow area), and the secondary flow loss is not considered. However, in the structure of the turbine blade, another main source of the loss of the airfoil profile of the turbine blade is the secondary flow loss in the airfoil end area (ie, the root area and the top area of ​​the turbine blade airfoil). This turbine blade airfoil structure, which does not consider the secondary flow loss, has the technical problems of low aerodynamic performance and high aerodynamic loss. Contents o...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/14
Inventor 邓国梁范小平孙奇钟刚云张晓丹钟主海
Owner DONGFANG TURBINE CO LTD
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