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Stator with adjustable vanes for the compressor of axial turbine engine

A turbine engine and compressor technology, which is applied to components of pumping devices for elastic fluids, engine control, engine components, etc., can solve the problems of large structure and turbine engine efficiency limitations, so as to improve efficiency and retain simplicity , the effect of precise positioning

Inactive Publication Date: 2018-03-13
SAFRAN AERO BOOSTERS SA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Currently, this architecture is particularly large
Furthermore, the efficiency of such turbine engines is limited

Method used

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  • Stator with adjustable vanes for the compressor of axial turbine engine
  • Stator with adjustable vanes for the compressor of axial turbine engine

Examples

Experimental program
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Effect test

Embodiment Construction

[0043] In the following description, the terms inner and outer refer to a position relative to the axis of rotation of the shaft turbine engine. The axial direction corresponds to a direction along the axis of rotation of the turbine engine. The radial direction is perpendicular to the axis of rotation. Upstream and downstream refer to the main flow direction of the flow in the turbine engine.

[0044] Whether a rotor or a stator, each blade has a leading edge, a trailing edge, an inner arc surface and an outer arc surface that joins the leading edge to the trailing edge, such as the chord of the blade. In the following description, reference may be made to the middle chord.

[0045] figure 1 A shaft turbine engine is shown in a simplified manner. In this particular case it is a twin-flow turbojet engine. The turbojet engine 2 comprises a first compression section known as a low-pressure compressor 4 , a second compression section known as a high-pressure compressor 6 , ...

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Abstract

The invention relates to an assembly for a stator (22) of a compressor of an axial-flow turbine engine, such as a low-pressure compressor of a turbojet engine also known as a booster. The assembly comprises: a first annular array of first vanes (26) of the stator (22) extending radially in the axial flow; and a second annular array of second vanes (28) of the stator (22), with controlled orientation, also known as variable-pitch vanes or VSV. In addition, the assembly comprises an external monobloc shroud on which the first vanes (26) and the second vanes (28) are mounted in a pivoting manner.

Description

technical field [0001] The invention relates to the field of stators with controlled-orientation blades for axial turbine engines. The invention also relates to a method of assembling a stator with adjustable vanes. The invention also relates to a shaft turbine engine, in particular a turbojet engine of an aircraft or a turboprop engine of an aircraft. Background technique [0002] Currently, several arrays of orientable vanes can be fitted to the stator housing of a compressor of a turbojet engine. Such blades may pivot during operation of the engine. Their curved blades are tilted relative to the main flow passing through them, allowing them to adjust their action based on engine conditions and flight conditions. Therefore, the operating range can be extended and efficiency can be optimized. [0003] The performance of the compressor is based on the accuracy of the angular positioning of the blades with respect to the casing, as well as the accuracy of the positioning ...

Claims

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Application Information

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IPC IPC(8): F04D29/56
CPCF04D29/563F05D2220/3217F05D2270/3061F01D17/162F01D25/24F05D2230/53F05D2240/12F05D2240/14F05D2240/80F05D2270/20F01D9/047F01D5/143F01D9/041F01D9/042F01D17/12
Inventor M.维韦
Owner SAFRAN AERO BOOSTERS SA
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