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Turbomachine blade having a maximum thickness law with high flutter margin

A maximum thickness, turbine technology, applied in the field of turbine blades, turbine rotor blades, can solve the problem of fan blade breakage, reduce fan flight conditions, damage to the engine, etc.

Active Publication Date: 2021-08-17
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Flutter can quickly amplify and cause fan blades to crack, or even damage the engine
[0016] Flutter is closely related to structural design, so it is difficult to eliminate or even limit flutter once it is detected during fan operation
[0017] Thus, it is still possible to prohibit certain areas of operation to limit the risk associated with flutter, but this will necessarily reduce the flight conditions under which the fan can operate

Method used

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  • Turbomachine blade having a maximum thickness law with high flutter margin
  • Turbomachine blade having a maximum thickness law with high flutter margin
  • Turbomachine blade having a maximum thickness law with high flutter margin

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0058] Turbine - General Description

[0059] refer to figure 1, schematically shows a turbine, more specifically an axial twin-flow turbojet 1 . The turbojet 1 shown comprises a fan 2 , a low-pressure compressor 3 , a high-pressure compressor 4 , a combustion chamber 5 , a high-pressure turbine 6 and a low-pressure turbine 7 .

[0060] The fan 2 and the low-pressure compressor 3 are connected to the low-pressure turbine 7 via a first transmission shaft 9 , while the high-pressure compressor 4 and the high-pressure turbine 6 are connected via a second transmission shaft 10 .

[0061] During operation, the combustion in the combustion chamber 5 is supplied with an air flow compressed by the low pressure compressor 3 and the high pressure compressor 4 , the expansion of the combustion gases of the combustion chamber drives the high pressure turbine 6 and the low pressure turbine 7 . Thus, by means of the shafts 9 and 10 the turbines 6 , 7 drive the fan 2 and the compressors 3 ...

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PUM

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Abstract

The invention relates to a turbomachine rotor blade which is characterized in that: - the ratio between the maximum thickness and the chord at 30% of the height of the blade is between 20% and 42% of the ratio between the maximum thickness and the chord at the blade root, - the ratio between the maximum thickness and the chord at 70% of the height of the blade is between 10% and 30% of the ratio between the maximum thickness and the chord at the blade root, - the ratio between the maximum thickness and the chord at 90% of the height of the blade is between 10% and 30% of the ratio between the maximum thickness and the chord at the blade root, - the ratio between the maximum thickness and the chord at the blade head is between 3% and 21% of the ratio between the maximum thickness and the chord at the blade root.

Description

technical field [0001] The present invention relates to the field of turbine blades and more particularly to the field of turbine rotor blades. [0002] In particular, the invention is intended for use in fans within turbojet engines or turbines. Background technique [0003] A turbomachine includes at least one bucket, such as, for example, a fan comprising a plurality of blades arranged radially about a central axis, for example around a disk. [0004] This type of vane forms the rotor when it is a moving vane or a bladed disk, or forms the stator. [0005] The vanes can be considered as protrusions relative to the continuous ring. Two adjacent vanes and rings define a gas flow path. [0006] The proximal end of each blade with respect to the central axis is commonly referred to as the blade root. In particular, the blade root is here considered to be the part of the blade located above the ring. [0007] The distal end is often called the blade tip. The distance bet...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/14
CPCF01D5/141Y02T50/60F05D2220/36F05D2240/301
Inventor 萨迪姆·迪尤登迈克尔·卡瓦雷克纪尧姆·帕斯卡·让-查尔斯·贡德雷尼古拉斯·皮埃尔·阿兰·埃德姆·德卡克雷-瓦门尼尔
Owner SAFRAN AIRCRAFT ENGINES SAS