Turbomachine fan flow-straightener vane, turbomachine assembly comprising such a vane, and turbomachine equipped with said vane or with said assembly

A technology of turbines and rectifiers, applied in the direction of supporting elements of blades, machines/engines, components of pumping devices for elastic fluids, etc., which can solve the problems of increasing vortex phenomena, noise, etc.

Active Publication Date: 2020-05-05
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The disadvantage of these sudden changes in direction is that these sudden changes in direction increase the vortex phenomenon which also causes noise

Method used

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  • Turbomachine fan flow-straightener vane, turbomachine assembly comprising such a vane, and turbomachine equipped with said vane or with said assembly
  • Turbomachine fan flow-straightener vane, turbomachine assembly comprising such a vane, and turbomachine equipped with said vane or with said assembly
  • Turbomachine fan flow-straightener vane, turbomachine assembly comprising such a vane, and turbomachine equipped with said vane or with said assembly

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Experimental program
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Embodiment Construction

[0029] figure 1 An aircraft turbine 100 to which the invention is applicable is shown. The turbine 100 is here a ducted turbine extending along the longitudinal axis X. A ducted turbine generally comprises an external nacelle 101 surrounding a gas generator 102, upstream of which a fan 103 is mounted. In the present invention and in a general manner, the terms “upstream” and “downstream” are defined with respect to the flow of gas in the turbine 100 . The terms "upper" and "lower" are defined with respect to a radial axis Z perpendicular to the axis X and with respect to the distance from the longitudinal axis X. The transverse axis Y is also perpendicular to the longitudinal axis X and the radial axis Z. These axes X, Y, Z form an orthonormal symbol.

[0030] In this example, the gas generator 102 includes, from upstream to downstream, a low pressure compressor 104 , a high pressure compressor 105 , a combustion chamber 106 , a high pressure turbine 107 and a low pressur...

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Abstract

The invention relates to a flow-straightener vane (1) of a bypass turbomachine (100) of longitudinal axis (X), the vane (1) comprising a plurality of vane sections (2) stacked radially with respect tothe axis (X) along a stacking line (L) between a root end (3) and a tip end (4), each vane section (2) comprising a pressure-face surface (7) and a suction-face surface (8) extending axially betweenan upstream leading edge (5) and a downstream trailing edge (6) and being tangentially opposed. According to the invention, between the leading (5) and trailing (6) edges of each vane section (2) there is formed a profile chord (CA) the length of which is substantially constant between the tip end (4) and the root end (3), and the stacking line (L) exhibits a curvature in a plane passing more or less through the axis (X) and through the stacking line (L), situated in the vicinity of the tip end (4) and oriented from downstream towards upstream.

Description

technical field [0001] The invention relates to the field of turbomachines. The present invention relates to turbine blades, and in particular to fan flow-straightener blades. The invention also relates to an assembly comprising a nacelle and a fan casing fixed to the nacelle and which fan casing is equipped with at least one rectifier blade, and to a turbine equipped with such a blade or such An assembly having straightener blades. Background technique [0002] Especially the natural evolution of multi-flow turbojet engines with fans upstream improves propulsion efficiency by reducing the specific thrust obtained by reducing the fan compression ratio, resulting in an increase in the bypass ratio (BPR) , the bypass ratio is the mass flow of air through one or more veins surrounding the gas generator calculated at maximum thrust when the engine is at rest at sea level in ISA The ratio of the mass flow of air. [0003] An increase in the bypass ratio affects the diameter o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/14F01D9/04F04D29/54F04D29/66
CPCF01D5/141F01D9/041F04D29/544F04D29/663F05D2250/38F05D2240/125F05D2220/323
Inventor 凯文·莫嘉娜·勒马钱德诺曼·布鲁诺·安德雷·若代纪尧姆·马丁劳伦特·苏拉特
Owner SAFRAN AIRCRAFT ENGINES SAS
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