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Apparatus for contouring gas turbine blades

A gas turbine blade and profile technology, which is applied in the directions of blade support elements, turbines, auxiliary devices, etc., can solve the problems of shortened blade chord length and difficult and precise machining.

Inactive Publication Date: 2016-08-31
LUFTHANSA TECH AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For this reason, the setting angle as well as the cross-section of the blade profile change, and the blade profile has a complex edge geometry, which can only be precisely machined with difficulty
[0013] In addition, the chord length of the blade is shortened through the profiling process since the commonly used cutting operations always remove the base material from the gas turbine blade

Method used

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  • Apparatus for contouring gas turbine blades
  • Apparatus for contouring gas turbine blades
  • Apparatus for contouring gas turbine blades

Examples

Experimental program
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Effect test

Embodiment Construction

[0063] exist figure 1 The device 1 according to the invention can be seen in FIG. 1 on a blade 2 which is part of a cascade ring or guide cascade ring of a compressor stage of a gas turbine, in particular an aircraft engine. The outer dimensions of the device 1 are such that the device can be fed in the flow channel towards the adjacent vane 2 without having to dismantle the vane 2 for this. The blade 2 can thus be contoured "on the wing", as a result of which the maintenance time during which the gas turbine cannot be used can be considerably shortened. When machining on a wing, contouring of the blade 2 is done while the blade 2 is installed in an engine suspended on the wing of an aircraft. Therefore, it is not necessary to disassemble the blade 2 from the engine for machining.

[0064] Each blade 2 has two edges 3a, a flow leading edge and a flow trailing edge. The device 1 can not only process the flow front edge and perform contour modification on the flow front edge...

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PUM

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Abstract

The invention relates to a device (1) for profiling a gas turbine blade (2), comprising at least one abutment (6a, 6b) arranged to bear against the gas turbine blade during profiling On the edge (3a) of (2); at least one side support (5a, 5b) arranged to bear in the transverse direction (7) on the gas turbine blade (2) during contour trimming on the suction side (3b) and / or pressure side (3c); and a machining unit (4) for machining a gas turbine blade (2), wherein the machining unit (4) is arranged to be purposefully The method melts at least a local area of ​​the edge (3a) such that the material solidifies into the new profile (18) substantially without adding additional material.

Description

technical field [0001] The invention relates to a device for contouring gas turbine blades. Background technique [0002] Blades in gas turbines, especially aircraft engines, are subject to wear during operation by aggressive particles such as sand or dust. [0003] In the front of the gas turbine, ie in the region of the compressor, erosion often leads to flattening of the leading edges of the compressor blades. In this case, the compressor blades of the first compressor stage, the so-called “fan blades”, are many times larger than the other blades of the engine. In the unworn state, the compressor blade has an aerodynamically optimized profile which is unfavorably changed due to wear. [0004] As a result of this degradation of the aerodynamic profile, the gas turbine becomes less efficient, that is to say, for the same performance, the gas turbine requires more fuel. [0005] From an economic point of view, it is therefore worthwhile to suppress the wear of the compres...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23P6/00B23Q9/00B24B19/14F01D5/00B23K26/352
CPCB23K26/354B23P6/002B23Q9/0014B24B19/14F01D5/005F05D2230/80B23K2101/001Y02T50/60B23K26/352B23K26/34B23P6/00B23P6/007B23K37/04F01D5/00B23Q1/25B23C3/00
Inventor S·策纳
Owner LUFTHANSA TECH AG