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Axial turbine compressor drum with double blade fixation

一种轴流式涡轮机、叶片的技术，应用在轴流式涡轮机的转子,轴流式涡轮机领域，能够解决昂贵机加工、复杂、结构庞大笨重等问题，达到表面简化的效果

Active Publication Date: 2019-04-30
SAFRAN AERO BOOSTERS SA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In addition, its implementation requires complex and expensive machining
In addition, its structure is bulky and bulky

Method used

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  • Axial turbine compressor drum with double blade fixation
  • Axial turbine compressor drum with double blade fixation
  • Axial turbine compressor drum with double blade fixation

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0037] In the following description, the terms inner or outer refer to a position relative to the axis of rotation of the axial turbine.

[0038] figure 1 A schematic representation of an axial turbine. In this case, it is a double-flow turbojet. The turbojet engine 2 comprises a first compression stage, a so-called low-pressure compressor 4 ; a second compression stage, a so-called high-pressure compressor 6 ; a combustion chamber 8 ; and one or more turbine stages 10 . In operation, the mechanical power of the turbine 10 is transmitted via the central shaft to the rotor 12 and drives the two compressors 4 and 6 . The speed change mechanism increases the rotational speed delivered to the compressor. Alternatively, different turbine stages can each be coupled to a compressor stage via respective concentric shafts. A compressor stage includes several rows of rotor blades associated with rows of stator blades. The rotation of the rotor about its axis of rotation 14 generate...

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Abstract

The invention relates to a rotor drum (40) of a low pressure compressor of an axial turbomachine. Said drum (40) comprises a wall (42) substantially rotationally symmetrical about its axis (14) and following a substantially curved profile. Said wall (42) is designed to support several blade rows (24, 26, 28). The first row of blades (24) is formed by means of an annular platform (46) integrally formed with the wall (42) at the highest point of the profile of the wall (42) with respect to the axis (14); (24) the second blade row (26) immediately downstream and the third blade row (28) immediately upstream of said first blade row (24) by means of one or more blade retaining grooves formed in said wall (54) FORMATION. Said first row of blades (24) and said drum form a monolithic assembly which eliminates some vibrations. Anchor blades are composite or hybrid. The rotor may be mounted in a housing with an annular stator.

Description

technical field [0001] The invention relates to a rotor of an axial turbine. More specifically, the present invention relates to a rotor drum of an axial turbomachine compressor. The invention relates to an axial flow turbine fitted with a low pressure compressor rotor drum. Background technique [0002] Turbines enable gases to be compressed, burned, and expanded. In this way the turbine provides mechanical energy. To perform these steps, a turbomachine includes a turbine and a compressor fitted with a rotor and housing. [0003] The inner surface of the housing and the outer surface of the rotor define the outline of the main flow path. It has variations in its annular cross-section. Its inner and outer profiles can increase and decrease in diameter along the axis of the engine. In compressors, especially low-pressure compressors, the outer casing usually has a diameter that decreases downstream. From upstream to downstream, the diameter of the rotor may increase an...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D29/32F04D29/34
CPCF04D29/322F04D29/023F01D5/06F01D5/063F01D5/3007F01D11/001
Inventor E.佩纳尔弗卡斯特罗
Owner SAFRAN AERO BOOSTERS SA
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