Solution heat treatment method for manufacturing metallic components of a turbo machine

A technology of solution heat treatment and metal parts, which is applied in the direction of engine components, blade support components, furnace components, etc., can solve the problems of inability to achieve material properties, conflicts, short retention time of thick sections, etc., and achieve good solution heat treatment Process, homogeneous temperature distribution, effect of reduced process variation

Inactive Publication Date: 2017-06-30
ANSALDO ENERGIA SWITZERLAND AG
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0013] In prior art, requirements for minimum cooling rate and risk of plastic deformation due to excessive temperature gradients during rapid cooling can be conflicting
Furthermore, the holding time at elevated temperature can vary within the component, since thin sections reach the holding temperature earlier than thick sections, thus, for example, due to insufficient (low) solutioning. To the extent that there can be a risk that the hold time in thick sections is too short to achieve the desired material properties

Method used

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  • Solution heat treatment method for manufacturing metallic components of a turbo machine
  • Solution heat treatment method for manufacturing metallic components of a turbo machine
  • Solution heat treatment method for manufacturing metallic components of a turbo machine

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Embodiment Construction

[0037] In a preferred embodiment, the invention is based on the combination of conditioning of complex components, preferably made of SX / DX-nickel-based or cobalt-based superalloys, to be processed in the application of inert gas flow Simultaneously a solution heat treatment (by wrapping a part of the part to control the heat flux) is carried out in the furnace with a specific positioning and installation of the part in the furnace. Components made from conventionally cast (CC) nickel- or cobalt-based superalloys can also be processed by the disclosed method.

[0038] The solution heated component is preferably a gas turbine component with internal cooling channels, preferably a turbine blade with an airfoil section with low thermal inertia and a root section with high thermal inertia, with an airfoil with low thermal inertia sections and guide vanes for 2 or 1 platform sections with large thermal inertia, or thermal shields.

[0039] figure 1 A simplified sketch of such a c...

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Abstract

A solution heat treatment method is disclosed for manufacturing metallic components 1 of a turbo machine, which components 1 provide a hot gas flow channel when assembled in the turbo machine after manufacturing, wherein the components 1 are subjected to a time-temperature-cycle in a furnace. The method includes positioning the components 1 in the furnace in a same principle as the component assembly in the turbo machine, but leaving flow areas and gaps 9 between neighbouring components; then starting the time-temperature-cycle; and applying an inert gas during the solution heat treatment process so that the inert gas flows through flow areas and gaps 9 for achieving a uniform temperature.

Description

technical field [0001] The present invention relates to a technique for manufacturing / heat treating metal parts. It relates to a solution heat treatment method for the manufacture of components, in particular components of turbomachines, such as a gas turbine according to the preamble of claim 1 . Such gas turbine components are, for example, turbine blades, guide vanes, or heat shields, especially cooled components. Background technique [0002] Such gas turbine components are subjected to high thermomechanical loads and are usually made of superalloys, for example nickel-based or cobalt-based superalloys. Single crystal (SX) and directionally solidified (DS) superalloys are less ductile (deformable) than conventionally cast (CC) parts. The low ductility of the SX and DS materials is further reduced in regions of high multiaxiality of the component. [0003] On the other hand, the thermomechanical loading of turbine blades requires a certain degree of ductility (deformab...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22F1/10C22F1/02
CPCC22F1/008C22F1/02C22F1/10F01D5/046F05D2300/606F05D2230/21F05D2230/40F01D25/145F05D2300/175F01D9/041F01D5/147C22F1/002F27D7/06F27D1/12F27D2009/0091F27D2007/063F01D25/005
Inventor M·施耐德M·巴里伊
Owner ANSALDO ENERGIA SWITZERLAND AG
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