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Compressor for an axial turbine engine with double counter-rotating rotors

A technology for turbine engines and compressors, which is applied to non-variable-capacity engines, engine components, components of pumping devices for elastic fluids, etc., can solve problems such as reduced compression rate and complexity, and achieve the effect of improving efficiency

Active Publication Date: 2019-04-16
SAFRAN AERO BOOSTERS SA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this scheme is complicated due to the number of constituent elements
Production and maintenance costs require considerable resources
Also, the compression ratio remains reduced

Method used

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  • Compressor for an axial turbine engine with double counter-rotating rotors
  • Compressor for an axial turbine engine with double counter-rotating rotors
  • Compressor for an axial turbine engine with double counter-rotating rotors

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0044] In the following, the terms "inner" or "inner" and "outer" or "outer" refer to a position relative to the axis of rotation of the axial turbine engine.

[0045] figure 1 Represents a simplified form of an axial turbine engine. In this case it is a ducted fan turbojet. The turbojet 2 comprises a first level of compression known as a low-pressure compressor 4 , a second level of compression known as a high-pressure compressor 6 , a combustion chamber 8 and one or more levels of turbines 10 . In operation, the mechanical power of the turbine 10 transmitted via the transmission shaft 11 to the rotor 12 causes the two compressors 4 to operate. The latter comprises rows of rotor blades associated with rows of stator blades. Thus, the rotation of the rotor about its axis of rotation 14 allows an airflow to be generated and progressively compressed up to the inlet of the combustion chamber 8 . A multiplier increases the rotational speed delivered to the compressor.

[0046...

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PUM

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Abstract

The invention relates to a compressor (4; 6) of an axial turbine engine (2) comprising two rotors (30; 32) or counter-rotating drums, each of an inner rotor (30) and an outer rotor (32) Blade rows (36; 40) forming a regular alternating pattern are provided. The inner rotor (30) is provided with a radial annular connection (48) fixed to the transmission shaft (11) from the turbine. The outer rotor (32) surrounds the inner rotor (30). The compressor (4) also includes a rotary bearing (60) coupled to the outer rotor (32) and arranged axially flush with the radial connection (48) so as to axially align the mechanical chain. This arrangement limits the action of centrifugal forces between the gaps between the blades (36; 40) and walls (34; 38) of the rotor (30; 32). The transmission device of the pinion (52) with a radial axis of rotation allows the outer rotor (32) to be driven by the inner rotor (30).

Description

technical field [0001] The field of the invention is turbine engines, in particular ducted fan turbojet aircraft for aviation applications. More precisely, the invention relates to the subject matter of a compressor for an axial turbine engine, in which the rotor is formed by two counter-rotating bladed parts. Background technique [0002] The use of counter-rotating rotors for compressors allows increasing the compression ratio and predetermined number of blade rows for a given length. This solution thus allows a shortening of the compressor and of the turbine engine containing the compressor, also achieving a substantial weight reduction. [0003] Document US20140286749 A1 discloses an axial turbine engine with a compressor formed by two counter-rotating rotors. Each rotor carries multiple rows of blades, the blades of the inner rotor alternating with the blades of the outer rotor. The inner rotor drives the outer rotor via a pinion, the axis of rotation of which is in ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D19/00F04D29/056F04D29/32F02K3/072
CPCF01D1/26F01D5/03F01D25/162F02C3/067F04D19/024F04D29/059F05D2240/54F05D2240/60F05D2260/40311F01D25/24F01D15/12F04D29/324F05D2220/30
Inventor C.克拉科
Owner SAFRAN AERO BOOSTERS SA
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