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Blade for a turbine engine propeller, in particular a propfan engine, propeller, and turbine engine comprising such a blade

A turbine engine, propeller technology, applied in the direction of propeller, engine components, engine control, etc., can solve problems such as not completely satisfactory, not efficient, etc.

Active Publication Date: 2016-09-28
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

[0016] However, the applicant has found that this alternative solution is not entirely satisfactory because it is not efficient regardless of the operational status (that is to say, the various phases of flight (takeoff, cruise, landing, etc.)

Method used

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  • Blade for a turbine engine propeller, in particular a propfan engine, propeller, and turbine engine comprising such a blade
  • Blade for a turbine engine propeller, in particular a propfan engine, propeller, and turbine engine comprising such a blade
  • Blade for a turbine engine propeller, in particular a propfan engine, propeller, and turbine engine comprising such a blade

Examples

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Embodiment Construction

[0045] figure 1 Shown schematically and by way of non-limiting example is an unducted fan turbine engine 1 according to the invention, from upstream to To the downstream comprises the compressor 2, the annular combustor 3, the high-pressure turbine 4, and the two counter-rotating low-pressure turbines 5 and 6, that is to say, the two low-pressure turbines 5 and 6 in two opposite directions with respect to the longitudinal axis L-L turn.

[0046] Each of the low-pressure turbines 5 and 6 is constrained to rotate with external propellers 7, 8 extending radially outside the nacelle 9 of the turbine engine 1, the nacelle 9 being substantially cylindrical and surrounding the compressor along the axis L-L 2. Combustion chamber 3, turbines 4, 5 and 6 extended. Combustion gases from the turbine are expelled through exhaust nozzles 10 to increase thrust.

[0047] The propellers 7 and 8 are arranged coaxially one after the other and comprise a plurality of blades 11A and 11B equiangu...

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Abstract

The invention relates to a blade (11A) for a turbine engine propeller, in particular a propfan engine, comprising a protruding part (16) on the leading edge (17) thereof, characterised in that said blade comprises means for controlling the position of the protruding part along the leading edge thereof.

Description

technical field [0001] The invention relates to a blade for a propeller of a turbine engine, in particular for a propeller of a turbine engine in the form of an unducted fan, and to a corresponding propeller and turbine engine. Background technique [0002] Although the present invention is particularly suitable for unducted fan turbine engines, implementations of the present invention are not limited to such applications. [0003] As is well known, an unducted fan turbine engine may comprise, upstream (front) and downstream (rear), respectively, two coaxially counter-rotating outer propellers, each of which is rotated by the turbine and substantially radially Extends outside the nacelle of the turbine engine. Each propeller generally includes a hub concentric with the longitudinal axis of the turbine engine, to which blades are fixed. [0004] The aerodynamic interference between the upstream and downstream contra-rotating propellers of such unducted fan turbine engines r...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C11/18F01D5/14
CPCF01D5/145B64D2027/005F01D5/148F05D2220/36F05D2240/303F05D2260/961F05D2270/62F05D2270/65F05D2270/64B64C11/18Y02T50/60F01D5/14F05D2260/96B64C11/48B64D27/10
Inventor 劳伦斯·弗朗辛·韦恩拉西卡·费尔南多诺曼·布鲁诺·安德雷·若代
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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