Tapered runner transonic turbine blade and turbine with same

A technology for turbine blades and transonic speeds, applied in the direction of blade support components, engine components, machines/engines, etc., can solve the problems of changing blade aerodynamic loss, shock wave loss affecting the suction surface boundary layer and wake development process, etc., to achieve comprehensive The effect of improving non-uniformity, reducing unsteady influence, and reducing total aerodynamic loss

Active Publication Date: 2015-03-18
INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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Problems solved by technology

This wave system structure is usually accompanied by a large velocity gradient and entropy increase, which not only produces shock wave loss

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  • Tapered runner transonic turbine blade and turbine with same
  • Tapered runner transonic turbine blade and turbine with same
  • Tapered runner transonic turbine blade and turbine with same

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[0028] In order to make the objectives, technical solutions, and advantages of the present invention clearer, the following further describes the present invention in detail with reference to specific embodiments and drawings. It should be noted that in the drawings or description of the specification, similar or identical parts use the same drawing numbers. The implementations not shown or described in the drawings are those known to those of ordinary skill in the art. In addition, although this article may provide an example of a parameter containing a specific value, it should be understood that the parameter does not need to be exactly equal to the corresponding value, but can be approximated to the corresponding value within acceptable error tolerances or design constraints. The directional terms mentioned in the embodiments, such as "upper", "lower", "front", "rear", "left", "right", etc., are only directions with reference to the drawings. Therefore, the directional ter...

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Abstract

The invention provides a tapered runner transonic turbine blade and a turbine with the same. A three-dimensional surface profile of the tapered runner transonic turbine blade is formed by N stacked blade profiles in the radial direction, wherein the N is more than or equal to 3; each N blade profile comprises a suction surface profile and a pressure surface profile; the suction surface profile of at least one blade profile is provided with a concave profile. By the tapered runner transonic turbine blade, the total aerodynamic loss of the blades is reduced, and flow loss of the transonic turbine in a supersonic region is effectively reduced.

Description

technical field [0001] The invention relates to the field of aerodynamics, in particular to a transonic turbine blade with a tapered channel with a concave suction surface without a cover section and a turbine using the same. Background technique [0002] Compared with traditional subsonic turbines, high-load transonic turbines can effectively increase the stage load, and have been widely used in high thrust-to-weight ratio aeroengines. Existing high-load transonic turbines (such as GE's E 3 Turbine, etc.) mainly adopts a tapered flow channel. After the airflow reaches the local sound speed at the throat, it continues to accelerate to exceed the local sound speed along the slightly convex or straight suction surface line in the uncovered channel. The outward and outward extensional shock waves and expansion waves generated by the supersonic airflow at the trailing edge and their respective reflection waves on the suction surface, together with the outward extensional shock ...

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Application Information

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IPC IPC(8): F01D5/14F01D5/02
Inventor 赵巍赵庆军赵晓路徐建中
Owner INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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