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Method for manufacturing gas turbine components

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

Active Publication Date: 2016-03-23
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 gas turbine components
  • Method for manufacturing gas turbine components
  • Method for manufacturing gas turbine components

Examples

Experimental program
Comparison scheme
Effect test

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 A further support structure 27 is also shown. usually, figure 1 The gas turbine 1 shown in is of conventional construction and comprises an air inlet 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 order. During operation, the high pressure compressor 5 is driven by the high pressure turbine 7 via a first hollow shaft, the 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, a low pressure (LP) turbine shaft (not shown), which is arranged coaxially within the first turbine shaft 10 . A coaxially arranged third shaft (not shown) is connected to a fan 12 which forces air into a...

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PUM

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Abstract

The invention relates to a method of manufacturing a gas turbine 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 therebetween. , wherein main gas channels for axial gas flow are defined between the elements (46, 46a, 46b), and wherein the component (37) has an inlet side for gas entry and an outlet side for gas outflow. The invention is characterized in that the method includes the step of machining a single metal blank to form a one-piece part (47) comprising: a portion (46b) of each element (46), wherein the portion (46b) relates to a part of the extended length of the element (46) between the ring structures (41, 42); and an annular member (42) connecting the element part (46b) and intended to form part of one of the ring structures . The invention also relates to a gas turbine (1) comprising a component (37) produced according to the method described above.

Description

technical field [0001] The invention relates to a method of manufacturing gas turbine components. In particular, the invention relates to a method involving the assembly of prefabricated parts. The invention also relates to a gas turbine comprising such a component. Background technique [0002] Axial gas turbines, such as aircraft "jet engines," typically include an air inlet, a compressor section, a fuel combustor, a turbine section, one or more rotatable drive shafts connecting the respective compressors and turbines, an exhaust outlet, and Used to support drive shafts and to mount engines to structures such as aircraft. [0003] Typically, the support structure is a static part comprising an inner housing or ring for connection to the bearings and a centrally located drive shaft, and an outer housing or ring for connection to, for example, an engine casing, And circumferentially distributed struts extend between and connect the inner shell / ring and the outer shell / rin...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D9/04F01D25/24F01D25/28F02C7/32
CPCF01D25/162F05D2230/53F05D2230/60F05D2230/232F02C7/20Y10T29/49234
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