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Turbomachine turbine blade comprising cooling circuit with improved homogeneity

一种涡轮机、叶片的技术，应用在移动叶片的冷却领域，能够解决冷却不均质等问题，达到提高冷却均质性的效果

Active Publication Date: 2017-02-22
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] During its investigative work, the applicant found in particular that the disadvantage of the known cooling circuit is the inhomogeneity of the cooling on each of the pressure side wall and the suction side wall of the blade

Method used

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  • Turbomachine turbine blade comprising cooling circuit with improved homogeneity
  • Turbomachine turbine blade comprising cooling circuit with improved homogeneity
  • Turbomachine turbine blade comprising cooling circuit with improved homogeneity

Examples

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Embodiment Construction

[0049] figure 2 A blade 30 for an aircraft turbine is shown according to a preferred embodiment of the present invention, generally comprising a blade root 32 to which an airfoil part 34 terminating at a tip 35 of the blade is connected on the opposite side of the blade root 32 . The blade root comprises a radially inner portion for retaining the blade in the rotor disk by a slip fit in a known manner. Furthermore, the blade root is connected to the airfoil part by an aerodynamic platform 36 which serves to internally define the main flow channel within the turbine.

[0050]In this description, the direction X is the direction corresponding to the direction of the engine axis when the blades 30 are mounted on the rotor disk inside the turbine wheel. Direction Z is a radial direction with respect to direction X, which merges with the direction of the length or span of the blade. The direction Y is such that the three directions X, Y and Z form an orthogonal reference coordin...

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PUM

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Abstract

The internal cooling of the moving blades of the turbines in aircraft turbomachines is limited in effectiveness because of inhomogeneities of this cooling on each of the pressure-face and suction-face walls. To address this problem, there is proposed a blade comprising a circuit (50) for cooling the airfoil part (34) thereof, in which the cavities interconnected in series are such that the stream of air flows radially toward the outside along the pressure-face wall (40) in pressure-face cavities (52, 56), and radially toward the inside along the suction-face wall (42) in a suction-face cavity (54) that is separated from the pressure-face cavities by an internal wall (58) of the airfoil part. In this way, the force of the Coriolis effect deflects the stream of air toward each of the pressure-face and suction-face walls thereby limiting the inhomogeneity.

Description

technical field [0001] The present invention relates to the field of aircraft turbines, and more particularly to the cooling of the moving blades of a turbine within such turbines. Background technique [0002] In turbines used to propel aircraft, the turbine blades are subjected to intense heat from the combustion gases in the combustion chamber. [0003] In order to protect the blades from such high temperatures, it is known to cool the blades by means of a cooling circuit formed by cavities arranged inside the airfoil part of the blades. These cooling circuits are usually supplied with relatively fresh air taken in at the compressor stage of the turbine. [0004] Nevertheless, continued improvements in the performance of aircraft engines lead to an increase in the temperature of these combustion gases. The temperature increase cannot be counteracted by improvements solely due to the materials and coatings forming the blade. [0005] Therefore, it is desirable to improv...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18
CPCF01D5/187F05D2260/221Y02T50/60F01D5/18F05D2220/323F05D2240/301
Inventor 夏洛特·玛丽·度久帕特里斯·埃尼奥塞巴斯蒂安·迪加尔·布鲁·德·奎萨特马修·让-卢克·沃勒布雷特
Owner SAFRAN AIRCRAFT ENGINES SAS
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