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Method for manufacturing of a gas turbine engine component

A gas turbine and component technology, applied in the field of assembling pre-manufactured parts and manufacturing gas turbine components, can solve problems such as difficult automation, time-consuming, inaccurate parts geometry, etc.

Active Publication Date: 2014-09-17
GKN AEROSPACE SWEDEN AB
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This heat leads to deformation of the final product and inaccurate geometry of individual parts
As a result, time must be spent on measurements and manual adjustments
As a result, assembling prefabricated parts is often difficult to automate in an efficient way

Method used

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  • Method for manufacturing of a gas turbine engine component
  • Method for manufacturing of a gas turbine engine component
  • Method for manufacturing of a gas turbine engine component

Examples

Experimental program
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Embodiment Construction

[0021] figure 1 An axial flow aircraft gas turbine 1 provided with a support structure 37 of components according to the invention is shown in a schematic general view. figure 1 An additional support structure 27 is also shown. usually, figure 1 The gas turbine 1 shown in is a conventional configuration and includes an air intake port 3, a low-pressure compressor 4, a high-pressure compressor 5, a combustion device 6, a high-pressure turbine 7, a low-pressure turbine 8 and an exhaust outlet 9 in axial flow sequence. During operation, the high-pressure compressor 5 is driven by the high-pressure turbine 7 via a first hollow shaft, a high-pressure (HP) turbine shaft (not shown). Similarly, the low-pressure compressor 4 is driven by the low-pressure turbine 8 via a second hollow shaft, namely a low-pressure (LP) turbine shaft (not shown), which is coaxially arranged in the first turbine shaft 10. A coaxially arranged third shaft (not shown) is connected to a fan 12, which forces a...

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PUM

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Abstract

The invention concerns a method for manufacturing of a gas turbine engine component (37) comprising an outer ring structure (42, 47), an inner ring structure (41), and a plurality of circumferentially spaced elements (46, 46a, 46b) extending between the inner ring structure (41) and the outer ring structure (42), wherein a primary gas channel for axial gas flow is defined between the elements (46, 46a, 46b), and wherein the component (37) has an inlet side for gas entrance and an outlet side for gas outflow. The invention is characterized in that the method comprises the step of machining a one-piece metal blank as to form a one-piece part (47) comprising: a portion (46b) of each of said elements (46), wherein said portion (46b) relates to a portion of an extension length of the elements (46) between said ring structures (41, 42); and a ring-shaped member (42) that connects said element portions (46b) and that is intended to form part of one of the ring structures. The invention also concerns a gas turbine engine (1) comprising a component (37) manufactured according to the above method.

Description

Technical field [0001] The invention relates to a method of manufacturing gas turbine components. In particular, the invention relates to a method involving assembling pre-manufactured parts. The invention also relates to a gas turbine comprising such a component. Background technique [0002] Axial gas turbines, such as aircraft "jet engines", usually include an air inlet, a compressor section, a fuel combustion chamber, a turbine section, one or more rotatable drive shafts connecting the corresponding compressor and turbine, an exhaust outlet, and Used to support the drive shaft and to install the engine to a structure such as an airplane. [0003] Generally, the support structure is a static part including an inner housing or ring and an outer housing or ring. The inner housing or ring is used to connect to the bearing and centrally positioned drive shaft, and the outer housing or ring is used to connect to, for example, the engine housing, And the pillars distributed circumf...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/04F01D25/24F01D25/28F02C7/32
CPCF01D25/162Y10T29/49234F05D2230/53F02C7/20F05D2230/232F05D2230/60F02C7/06
Inventor 拉尔斯-奥洛夫·赫尔格伦奥洛夫·莱温肯特·霍梅达尔
Owner GKN AEROSPACE SWEDEN AB