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Composite Curved Vanes for Multistage Axial Compressors

An axial-flow compressor and vane technology, which is applied to the components of the pumping device for elastic fluid, mechanical equipment, machine/engine, etc. The effect of margin, balanced spanwise load distribution

Active Publication Date: 2019-08-16
SHANGHAI ELECTRIC GAS TURBINE CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, since the curved vane is mainly used to control the flow separation in the corner area, the reverse bending has not been applied in the gas turbine compressor

Method used

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  • Composite Curved Vanes for Multistage Axial Compressors
  • Composite Curved Vanes for Multistage Axial Compressors

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Embodiment Construction

[0022] The specific implementation manners of the present invention will be described in further detail below in conjunction with the accompanying drawings. These embodiments are only used to illustrate the present invention, not to limit the present invention.

[0023] In the description of the present invention, it should be noted that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", " The orientations or positional relationships indicated by "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. are based on the orientation or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying Describes, but does not indicate or imply that the device or element referred to must have a specific orientation, be constructed in a specific orientation, and operate in a specific orientation, and therefore should not be construed as limiting the inventio...

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Abstract

The invention relates to the technical field of gas turbines, in particular to a composite bent stationary blade for a multi-stage axial flow gas compressor. The composite bent stationary blade comprises a stationary blade body. The stationary blade body comprises a blade root part, a blade middle part and a blade tip part. The blade middle part is located between the blade root part and the blade tip part. The gravity center overlapping axis of the blade middle part extends in the radial direction of a main shaft of the multi-stage axial flow gas compressor. The blade root part is forwardly bent towards a force absorption face, and the blade tip part is reversely bent towards a pressure face. The form that the blade root part is forwardly bent and the blade tip part is reversely bent is adopted, and when the composite bent stationary blade is applied to the multi-stage axial flow gas compressor, flow separation of the root part of the stationary blade can be remarkably improved, spanwise load distribution of the stationary blade can be balanced, the stall margin of the stationary blade can be improved, and stationary blade losses can be reduced; and the stable work range of the transonic movable blade tip part can be widened, and therefore flow losses are reduced within the whole spanwise range, and the stall margin of the transonic stage is expanded.

Description

technical field [0001] The invention relates to the technical field of gas turbines, in particular to a composite curved vane for a multi-stage axial flow compressor. Background technique [0002] Existing gas turbine compressors generally adopt three-dimensional blade design technology, that is, by changing the center of gravity stacking axis of the blade or the relative blade characteristics of each section to realize the geometric forms such as blade bending and sweeping, so as to effectively control the strong three-dimensional flow inside the compressor and reduce the flow rate. losses, delay flow separation, improve compressor efficiency and stall margin. However, due to the complexity of the three-dimensional viscous flow field inside the compressor, the mechanism of the influence of the curved blades on the flow has not yet been definitely explained. [0003] The curved stator blades currently used in gas turbine compressors all adopt the geometric form of the root ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D29/54
CPCF04D29/544
Inventor 朱芳赵连会何磊
Owner SHANGHAI ELECTRIC GAS TURBINE CO LTD
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