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Turbine engine stage

A turbine engine and casing technology, applied in the direction of engine components, machines/engines, liquid fuel engines, etc., can solve problems such as fracture, and achieve the effect of improving mechanical strength and reducing noise

Inactive Publication Date: 2013-12-04
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

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Method used

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  • Turbine engine stage
  • Turbine engine stage
  • Turbine engine stage

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Embodiment Construction

[0026] First refer to figure 1 , the figure shows a fan 10 of a turbine engine along axis 2, said fan comprising a rotor consisting of a disc 14 with a plurality of blades 16 around it, the blade roots being mounted in slots of the disc 14, The blade profiles 18 extend radially outwards to a fan case 20 which in turn is integral with a nacelle 22 which surrounds the blades 16 on the outside. The fan wheel is rotated about the engine axis 12 by a shaft 24 which is fixed by bolts 26 to a frustoconical wall 28 which in turn is fixed to the fan wheel. The shaft 24 is supported and guided by a bearing 30, and the bearing 30 is mounted on the upstream end of an annular support 32, and the annular support 32 is fixed to the downstream of an intermediate casing (not shown in the figure), and the intermediate casing is arranged on the low-pressure compressor 34 Downstream, the rotor 36 of the latter is fixed via a connecting wall 38 to the fan wheel.

[0027] On the inner surface, th...

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Abstract

A turbine engine stage including a rotor wheel including a plurality of blades surrounded on an outside by a casing including a layer of abradable material on its inside surface facing free ends of the blades. At least one plane sensor for measuring clearance at blade tips is carried by the inside surface of the casing and is covered by the layer of abradable material.

Description

technical field [0001] The invention relates to a stage of a turbine engine including a rotor wheel and means for monitoring tip clearance. Background technique [0002] Typically, a bypass turbine engine includes, from upstream to downstream: a fan, at the outlet of which the airflow is divided into the main airflow that flows inside the turbojet engine through the compressor, combustion chamber and turbine, and the airflow that flows around the turbojet engine secondary airflow. [0003] The fan consists of a rotor wheel comprising a plurality of blades carried on its periphery, regularly spaced about the axis of the disk. The receiver surrounds the outside of the blade. To prevent air from passing over the blade tips, which would reduce the efficiency of the engine, a layer of wear resistant material is used on the inside surface of the fan case, which is positioned flush with the fan blades. [0004] During operation, it is important to monitor the clearance between t...

Claims

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Application Information

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IPC IPC(8): F01D11/12G01B7/14F01D21/00F04D27/00
CPCG01B1/00F01D21/003Y02T50/672F01D25/24F04D29/164F01D11/122F04D27/001G01B7/14Y02T50/60
Inventor 飞利浦·查尔斯·奥克塔夫·拜勒安德鲁·勒鲁克斯大卫·托林克里斯蒂安·兰纳瑞飞利浦·萨拿戈塞巴斯蒂安·伯纳德
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A