Split top end with annular de-icing duct for low pressure compressor of an axial turbine

An axial-flow turbine and compressor technology, applied in the field of low-pressure compressors, can solve problems such as pipe rupture, and achieve the effects of promoting expansion, reducing the risk of rupture, and reducing mechanical constraints

Active Publication Date: 2019-01-29
SAFRAN AERO BOOSTERS SA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the rigid connection of the annular duct with respect to the casing creates a risk involving rupture of the conduit

Method used

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  • Split top end with annular de-icing duct for low pressure compressor of an axial turbine
  • Split top end with annular de-icing duct for low pressure compressor of an axial turbine
  • Split top end with annular de-icing duct for low pressure compressor of an axial turbine

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Embodiment Construction

[0041] In the following description, the terms "inner" or "inner" and "outer" or "external" refer to a position relative to the axis of rotation of the axial turbine. The axial direction corresponds to a direction along the axis of rotation of the turbine. The radial direction is perpendicular to the axis of rotation.

[0042] figure 1is a simplified illustration of an axial turbine 2 for an aircraft. In this case it is a twin-flow turbocharger. The turbocharger 2 includes a first compression stage called a low-pressure compressor 4 , a second compression stage called a high-pressure compressor 6 , a combustion chamber 8 and one or more turbine stages 10 . During operation, the mechanical power of the turbine 10 is transmitted via a central shaft to the rotor 12 which moves the two compressors 4 and 6 . These compressors include rows of rotor blades associated with associated rows of stator blades. The rotation of the rotor about its axis of rotation 14 thus allows an ai...

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PUM

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Abstract

The invention comprises a splitter nose of an axial turbomachine, in particular a compressor, the splitter nose comprising: an annular casing an annular conduit for de-icing a separation edge of the splitter nose; the conduit is connected to the casing only in a first zone in the region of a hot air inlet and in a second zone located in a position diametrically opposite the inlet, or forming relative to the axis of the turbomachine an angle α less than 30° with respect to the position so as to allow expansion deformations of the conduit. The invention also comprises a compressor and a turbomachine comprising such a splitter nose.

Description

technical field [0001] The invention relates to the field of axial turbomachines. More specifically, the present invention relates to a split tip for a low pressure compressor of an axial turbine comprising an annular deicing duct. The invention also relates to a low pressure compressor. Background technique [0002] The split tip of the low pressure compressor of an aircraft turbine comprises a split edge which is subjected to ice accumulation during flight. This ice accumulation originates from flight conditions, especially from high-altitude temperatures. Ice that breaks away from the separation edge can be sucked into the compressor and damage the turbine, and accumulated ice can also reduce the output of the turbine. In order to overcome this phenomenon, it is known to provide a split head with de-icing means by circulating hot air in the circulating head. [0003] Published patent document EP0918150A1 discloses a split tip of a turbomachine comprising an annular ca...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/047
CPCB64D2033/0233F02C7/047F01D25/02F04D29/584F05D2260/30B64D15/04B64D33/02F01D25/10F04D29/522F04D29/542F04D29/545F05D2220/323F05D2250/141
Inventor J-F.科特奎斯
Owner SAFRAN AERO BOOSTERS SA
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