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Turbomachine casing and impeller

A turbine engine, rotor wheel technology, applied in the direction of engine components, machines/engines, liquid fuel engines, etc., can solve the problems of reducing blades, reducing the surface area of ​​blades, reducing the efficiency of rotor wheels, etc.

Active Publication Date: 2015-06-10
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0011] However, this requires reducing the surface area of ​​the blades, which in turn reduces the work done by the blades on the fluid, thereby reducing the efficiency of the rotor wheel

Method used

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  • Turbomachine casing and impeller
  • Turbomachine casing and impeller
  • Turbomachine casing and impeller

Examples

Experimental program
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Embodiment Construction

[0044] figure 1 An axial compressor 10 for a turbine engine is shown. The axial compressor includes a housing 12 having a rotor wheel 14 mounted therein. In conventional manner, the rotor wheel 14 itself comprises a rotor disk 16 having radial blades 18 fastened thereto in an axisymmetric manner. The rotor wheel is arranged rotatable about an axis of rotation A inside the housing 12 .

[0045] The housing 12 has an inner wall 20 that defines a gas flow passage. This inner wall forms a surface of revolution, generally substantially conical in shape, and in the present example cylindrical, wherein said surface of revolution is in axial registration with rotor wheel 14 .

[0046] exist Figure 2 to Figure 7 The arrangement of the blades 18 and the arrangement of the inner wall 20 of the housing 12 of the present invention are shown for various embodiments.

[0047] In the various figures, the same or similar elements are marked with the same reference numerals. In addition,...

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PUM

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Abstract

The invention concerns an assembly comprising a turbomachine casing (12) and an impeller (14) arranged therein. The housing (12) has an internal wall (20) comprising a circumferential strip (24) of abradable material. Facing the ends of the vanes, the housing has, upstream, the strip of abradable material, and downstream, a circumferential groove (30). The strip of abradable material is defined downstream by the circumferential groove (30). The downstream limit of the circumferential groove (30) is located to the right of or downstream from the trailing edge (18B) of the vanes (18). This arrangement optimises the use of abradable material in the turbomachine casing.

Description

technical field [0001] The invention relates to an assembly comprising a turbine engine casing and a bladed rotor wheel arranged in said casing. Background technique [0002] The housing may house one or more rotor wheels mounted for rotation inside the housing. [0003] In order to optimize the efficiency of the turbine engine, the blades are generally arranged in such a way that their tips pass as close as possible to the inner wall of the housing. [0004] Specifically, especially during the first hours of operation of an aeroengine for an airplane or helicopter, there is sometimes a gap between the tip of the blade and the casing due to thermal expansion of the blade or elongation of the blade under the action of centrifugal force. Inner wall contact. [0005] In order to avoid such contact that damages the walls of the casing, it is known that the inner surface of the turbine engine casing is sometimes provided with a strip of abradable material (i.e. a material place...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/16F01D11/12F04D29/52
CPCF01D11/122F04D29/164F04D29/526F01D25/24
Inventor V·P·G·佩罗特S·科孔
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A