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Fan blade with composite core and wavy wall trailing edge cladding

一种复合芯、后缘的技术，应用在复合转子和定子翼型件领域，能够解决发动机性能和发动机效率损失等问题

Inactive Publication Date: 2013-06-26
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The creation of such wakes can result in loss of engine performance and engine efficiency

Method used

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  • Fan blade with composite core and wavy wall trailing edge cladding
  • Fan blade with composite core and wavy wall trailing edge cladding
  • Fan blade with composite core and wavy wall trailing edge cladding

Examples

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Embodiment Construction

[0016] Shown in Figure 1 is an exemplary aircraft turbofan gas turbine engine 10, which is defined around an engine centerline axis 12 and is suitably designed to be mounted on the wing or fuselage of an aircraft. In continuous flow communication downstream, the engine 10 includes a fan 14, a supercharger 16, a high-pressure compressor 18, a combustor 20, a high-pressure turbine (HPT) 22, and a low-pressure turbine (LPT) 24. The HPT or high-pressure turbine 22 is connected to the high-pressure compressor 18 through a high-pressure drive shaft 23. The LPT or low-pressure turbine 24 is connected to both the fan 14 and the supercharger 16 through a low-pressure drive shaft 25.

[0017] In a typical operation, the air 26 is pressurized by a row of fan blades 11 in the fan 14 and generates an internal air flow 15 which is directed through the supercharger 16 which further pressurizes the internal air flow 15. The pressurized air then flows into the high pressure compressor 18 which f...

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Abstract

A gas turbine engine airfoil includes leading and trailing edges (LE, TE), pressure and suction sides extending from airfoil base to airfoil tip, trailing edge cladding made of cladding material bonded to composite core (44) made of composite material, cladding material less brittle than composite material, composite core including central core portion extending downstream from leading edge portion to trailing edge portion of composite core (44), and trailing edge cladding including wavy wall and trailing edge (TE). Pressure and suction side flanks of trailing edge cladding may be bonded to pressure and suction side surfaces of trailing edge portion. Waves of wavy wall may extend normal to and away from the pressure and suction side surfaces. Trailing edge cladding may include wavy pressure and suction side trailing edge guards including waves of wavy wall. Airfoil may extend outwardly from platform of a blade. Root may include integral dovetail.

Description

Technical field [0001] The present invention relates to rotor and stator airfoils of rotary machinery and gas turbine engines, in particular to composite rotor and stator airfoils. Background technique [0002] Aircraft turbine engines and other types of rotating machinery include fixed airfoils and rotating airfoils that direct airflow downstream. Therefore, a wake can be generated and directed downstream, where it can hit objects downstream of the airfoil. Wake impacts can create undesirable noise and / or aerodynamic loads. Unpleasant noises can be caused by the wake of the upstream rotating airfoil hitting the stator or rotor component downstream of the rotating airfoil or the wake of the upstream stator airfoil hitting the rotating airfoil downstream of the stator airfoil. [0003] The generation of such wakes can result in loss of engine performance and engine efficiency. The reduction of wake amplitude can reduce the noise and aerodynamic load generated when the wake hits d...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/32F04D29/38
CPCF01D5/141F01D5/282F05D2220/36F05D2240/304F05D2250/184Y02T50/60
Inventor N.J.克雷D.E.莫尔曼D-J.辛T.H.伍德
Owner GENERAL ELECTRIC CO
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