High temperature alloy material for engine turbine and preparation method thereof

A superalloy and engine technology, applied in the field of superalloys, can solve the problems of easy expansion of fatigue cracks, deterioration of hot workability, low-cycle fatigue performance, etc., and achieve excellent machinability, quality and performance assurance, and good microstructure stability. Effect

Active Publication Date: 2015-08-26
北京金恒博远科技股份有限公司
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AI Technical Summary

Problems solved by technology

As the degree of alloying of the turbine disk continues to increase, severe segregation deteriorat

Method used

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Embodiment 1

[0031] A superalloy material for an engine turbine, the composition of the superalloy material includes by weight percentage: C: 0.265%, Mn: 2.18%, Si: 0.54%, Cr: 18.7%, Mo: 9.3%, W: 3.68 %, Al: 0.28%, Cu: 0.21%, Fe: 6.5%, B: 1.05%, Ti: 3.33%, Co: 6.81%, Zr: 0.16%, Nb: 1.21%, the balance is Ni and unavoidable Impurities, the manufacturing method of the superalloy material for the engine turbine, comprising the following steps:

[0032] (1) Raw material preparation: batching according to the above alloy composition;

[0033] (2) Smelting electrode rods, smelting the raw materials to control the vacuum degree of 0.1Pa, keep the melting power unchanged for 37 minutes after all the raw materials are melted; increase the vacuum degree to 0.008Pa, refine at 1635°C for 12 minutes, adjust the composition to meet the requirements, Then adjust to 1555°C and pour into consumable electrode rods;

[0034] (3) Electroslag remelting: the ratio of slag material for electroslag remelting is:...

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PUM

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Abstract

The invention relates to a high temperature alloy material for an engine turbine. The high temperature alloy material comprises components according to weight percentage: 0.22-0.28% of C, 2.1-2.2% of Mn, 0.45-0.61% of Si, 18.3-19.2% of Cr, 8.25-10.4% of Mo, 3.50-3.80% of W, 0.05-0.35% of Al, 0.18-0.27% of Cu, 5.0-9.2% of Fe, 1.0-1.1% of B, 3.15-3.45% of Ti, 6.7-8.2% of Co, 0.12-0.18% of Zr, 1.12-1.38% of Nb, and the balance of Ni and inevitable impurities, and a preparation method which is matched with the material is provided. The prepared blank is reasonable in component design, and is matched with characteristics of reasonable thermal processing technology, convenient production organization, strong field operability and strong apparatus universality, so that the quality of the produced high temperature alloy large-sized turbine disk product is high, the structure property meets the standard requirements, the production efficiency is high, and the economic benefit and the social benefit are obvious.

Description

technical field [0001] The invention belongs to the field of high-temperature alloys, and specifically relates to a high-temperature alloy and a preparation method thereof, which are mainly applicable to high-temperature alloy materials for engine turbines and a preparation method thereof. Background technique [0002] Superalloys refer to a class of metal materials developed based on iron, cobalt, and nickel that can serve at high temperatures above 600°C. The superalloy is a single austenite matrix structure, has high high temperature strength, oxidation resistance and corrosion resistance, and has good structural stability and service reliability. It is also called thermal strength alloy and thermal stability superalloy. It is often used abroad Called superalloy (Superalloy). [0003] Superalloys can be classified in different ways according to the alloy composition, structure and forming process. According to the classification of matrix elements, there are mainly nick...

Claims

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Application Information

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IPC IPC(8): C22C19/05C22B9/18C22F1/10
Inventor 邢桂生
Owner 北京金恒博远科技股份有限公司
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