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High-specific-creep-strength nickel base single crystal high-temperature alloy and preparation method and application thereof

A creep strength, nickel-based single crystal technology, applied in the preparation of aeroengine turbine blades, high specific creep strength nickel-based single crystal superalloy and its preparation field, can solve the problems of high density and high cost, Achieve the effect of low density, high temperature bearing capacity and low cost

Active Publication Date: 2016-04-20
谷月恒
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The purpose of the present invention is to solve the problems of high density and high cost in the second generation single crystal Ni-based superalloy in the prior art, and provide a low density, low cost, good thermal stability and high specific creep Strong high-performance low-density Ni-based single crystal superalloy and its preparation method and application in the preparation of aeroengine turbine blades

Method used

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  • High-specific-creep-strength nickel base single crystal high-temperature alloy and preparation method and application thereof
  • High-specific-creep-strength nickel base single crystal high-temperature alloy and preparation method and application thereof
  • High-specific-creep-strength nickel base single crystal high-temperature alloy and preparation method and application thereof

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Embodiment 1～4

[0041] Embodiment 1~4 and comparative example

[0042] See Table 1 for the chemical composition of the examples of the present invention and the comparative examples of known Ni-based single crystal superalloys.

[0043] Specific preparation method:

[0044] The first step: the alloy is smelted in a vacuum induction furnace, first cast into various Ni-based superalloy master alloys whose chemical composition meets the requirements, and cast to prepare master alloy rods;

[0045] Step 2: Remelt the master alloy bar through directional solidification equipment, and then use the seed crystal method to pass through the Brizmann (Bridgeman) directional solidification technology, at a temperature gradient of 100°C / cm and a pulling rate of 3mm / min Preparation of single crystal test rod;

[0046] The third step: the single crystal test rod prepared in Examples 1 to 4 was subjected to solid solution treatment for 4 hours in the range of 1310-1330° C., followed by air cooling; then ca...

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Abstract

The invention discloses a high-specific-creep-strength nickel base single crystal high-temperature alloy, a preparation method thereof and application thereof to preparation of aircraft engine turbine blades. The high-specific-creep-strength nickel base single crystal high-temperature alloy is characterized by comprising the following components (wt%): 7-9.5% of Cr, 0.4-1.0% of W, 0.5-3.5% of Ta, 4.0-7.0% of Mo, 5.5-7.0% of Al, 0.4-2.0% of Ti, 0.9-2.0% of Nb, 2.0-5.0% of Co, 0.05-0.15% of Hf, and the balance of Ni. The alloy is obtained through smelting by a vacuum induction furnace, remelting, directional solidification and heat treatment. Compared with a traditional other second-generation nickel base single crystal high-temperature alloy, the high-specific-creep-strength nickel base single crystal high-temperature alloy is better in creep performance, but obviously reduces the density and the cost, can be applied to preparation of the aircraft engine turbine blades, and can satisfy the design demands of modern high-thrust-weight-ratio aircraft engines.

Description

technical field [0001] The invention relates to the field of nickel-based single crystal superalloy and its preparation, in particular to the application of a nickel-based single crystal superalloy with high specific creep strength and its preparation method in the preparation of aeroengine turbine blades. Background technique [0002] With the development of aero-engines towards high thrust-to-weight ratios, the temperature and internal pressure at the front inlet of the engine turbine continue to increase, requiring higher temperature-bearing capabilities for engine hot-end components such as turbine blades and guide vanes. Therefore, these hot-end components must be used Superalloys are prepared. [0003] Nickel (Ni)-based alloys can use a variety of strengthening methods to improve the temperature bearing capacity of the alloy, such as using a variety of high melting point / noble metal elements (tungsten (W), molybdenum (Mo), cobalt (Co), chromium (Cr), Rhenium (Re), rut...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22C19/05C30B29/52C30B11/00C30B33/02C22F1/10
CPCC22C19/057C22F1/10C30B11/00C30B29/52C30B33/02
Inventor 谷月峰
Owner 谷月恒
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