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Turbine components or groups of components with non-axisymmetric surfaces

A technology for turbines and components, which is applied to the components of pumping devices for elastic fluids, engine components, supporting components for blades, etc., and can solve problems such as the degradation of fan flow performance

Active Publication Date: 2018-01-02
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] However, it was found that such non-axisymmetric channels degrade the flow performance through the fan

Method used

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  • Turbine components or groups of components with non-axisymmetric surfaces
  • Turbine components or groups of components with non-axisymmetric surfaces
  • Turbine components or groups of components with non-axisymmetric surfaces

Examples

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Embodiment Construction

[0063] refer to Figure 3a , the part 1 of the turbine (if it is not a single piece, then a set of parts) has at least two adjacent blades 3E, 3I and a platform 2 from which the blades 3E, 3I extend. The term platform is here to be interpreted in a broad sense and generally designates any element of a turbine which can be mounted (radially extending) with blades 3E, 3I and which has walls against which air circulates.

[0064] In particular, the platform 2 may be one-piece, or may be formed by a plurality of basic parts each supporting a single blade 3E, 3I (the "root" of the blade) in order to constitute Figure 3a vanes of the type shown in . In the example shown, these are "add-on" platforms, ie platforms separate from the buckets (they are separate components). There are also "integrated" platforms (to be mentioned again later) where each blade is bonded to a "half" platform and the junction between two adjacent platforms is made in the middle of the channel . It shoul...

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PUM

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Abstract

The invention relates to a component (1) or set of components of a turbomachine comprising at least: a first blade and a second blade (3I, 3E) and a platform (2) from which the blades (3I, 3E) extend, characterized in that the platform (2) have a non-axisymmetric surface (S) bounded by a first end plane and a second end plane (PS, PR) and defined by at least two construction curves of class C, each of which represents the value of the radius of said surface (S) depending on the pressure surface of the first blade (3I) and the pressure surface of the second blade (3E) in a plane substantially parallel to said end plane (PS, PR) Where between the suction surfaces, the construction curves include: at least one upstream curve and one downstream curve; each construction curve is defined by at least one pressure surface control end point and one suction surface control end point such that: the downstream curve is at the suction surface The tangent at the control end point 20 is inclined by at most 5°; the other tangents of the construction curve at the control end point are inclined by at least 5°.

Description

technical field [0001] The invention relates to a turbomachine component comprising a blade and a platform with non-axisymmetric surfaces. Background technique [0002] A fan is a large diameter rotating part at the inlet of a twin-flow turbine formed by a generally conical hub (spinner) to which are attached radially extending blades, as in figure 1 (Reference number 1) is visible on the left. The fan compresses a large mass of cool air which is partly injected into the compressor and the rest of the cool air forms a cylindrical flow around the engine and directed towards the rear for thrust generation. [0003] Optimization of production and performance of fans requires, inter alia, an increase in the rate of mass flow across the blades. [0004] To increase this mass flow rate, it is possible to modify the parameters of the fan blades, or to modify the walls of the vein, that is, the entire passage between the blades for fluid flow (in other words, the inter-blade porti...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/14
CPCF01D5/143F01D5/14F04D29/32F04D29/329
Inventor 本杰明·鲁克沃斯基埃斯特班·贝尔纳尔多斯-沙马涅马修·让·卢克·沃勒布雷特
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A