Silicon oxide-based ceramic core for large-size directional hollow blade of heavy-duty gas turbine and preparation of silicon oxide-based ceramic core

A technology of hollow blades and ceramic cores, applied in cores, casting molding equipment, casting molds, etc., can solve problems such as poor creep resistance, large firing shrinkage, and slow core removal speed, so as to improve high temperature performance, The effect of reducing sintering shrinkage and increasing the rate of core removal

Pending Publication Date: 2022-03-29
SHENYANG RES INST OF FOUNDRY
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] Aiming at the problems of large firing shrinkage, poor creep resistance, large size deviation, and slow core removal speed of the above-mentioned silica-based ceramic core, the present invention provides a silica-based ceramic core for large-size directional hollow blades of heavy-duty gas turbines. Ceramic core and preparation method thereof

Method used

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  • Silicon oxide-based ceramic core for large-size directional hollow blade of heavy-duty gas turbine and preparation of silicon oxide-based ceramic core

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Experimental program
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Effect test

Embodiment 1

[0034] A method for preparing a silicon oxide-based ceramic core for a large-size directional hollow blade of a heavy-duty gas turbine, comprising the following process steps:

[0035] 1. Weigh the powder: Weigh a certain weight of quartz glass powder (SiO 2 Content is 99.9%), zircon powder, aluminum oxide powder and calcium carbonate powder are put into ball mill jar. In the powder, take by weight percentage 20% 200 mesh quartz glass powder, 20% 400 mesh quartz glass powder, 20% 600 mesh quartz glass powder, 30% zircon powder, 5% alumina powder, 5% % calcium carbonate powder.

[0036] 2. Ball mixing: Add 0.5% of oleic acid by weight of the powder, add alumina ceramic balls and mix according to the ball-to-material ratio of 2:1, and the ball mixing time is 4 hours to obtain the mixed powder.

[0037] 3, mix plasticizer: take by weighing the plasticizer that accounts for 16% of mixed powder weight described in step 2, the composition of plasticizer is 90% paraffin, 5% beeswax...

Embodiment 2

[0044] A method for preparing a silicon oxide-based ceramic core for a large-size directional hollow blade of a heavy-duty gas turbine, comprising the following process steps:

[0045] 1. Weigh the powder: Weigh a certain weight of quartz glass powder (SiO 2 Content is 99.95%), zircon powder, aluminum oxide powder and calcium carbonate powder are put into ball mill jar. In the powder, take by weight percentage 25% of 200 mesh quartz glass powder, 35% of 400 mesh quartz glass powder, 30% of 600 mesh quartz glass powder, 6% of zircon powder, 3% of alumina powder, 1 % calcium carbonate powder.

[0046] 2. Ball mixing: Add 0.2% of oleic acid by weight of the powder, add alumina ceramic balls and mix according to the ball-to-material ratio of 2:1, and the ball mixing time is 6 hours to obtain the mixed powder.

[0047] 3, mix plasticizer: take by weighing the plasticizer that accounts for 18% of mixed powder weight described in step 2, the composition of plasticizer is 93% paraff...

Embodiment 3

[0065] A method for preparing a silicon oxide-based ceramic core for a large-size directional hollow blade of a heavy-duty gas turbine, comprising the following process steps:

[0066] 1. Weigh the powder: Weigh a certain weight of quartz glass powder (SiO 2 Content is 99.99%), zircon powder, aluminum oxide powder and calcium carbonate powder are put into ball mill jar. In the powder, take by weight percentage 30% of 200 mesh quartz glass powder, 40% of 400 mesh quartz glass powder, 25% of 600 mesh quartz glass powder, 4% of zircon powder, 0.5% of alumina powder, 0.5 % calcium carbonate powder.

[0067] 2. Ball mixing: Add 0.1% of oleic acid by weight of the powder, add alumina ceramic balls and mix according to the ball-to-material ratio of 2:1, and the ball mixing time is 10 hours to obtain the mixed powder.

[0068] 3, mix plasticizer: take by weighing the plasticizer that accounts for 20% of mixed powder weight described in step 2, plasticizer is composed of 94.5% paraff...

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Abstract

The invention relates to a silicon oxide-based ceramic core for a large-size directional hollow blade of a heavy gas turbine and a preparation method of the silicon oxide-based ceramic core. The silicon oxide-based ceramic core adopts quartz glass powder as a base material, and adopts zircon powder, alumina powder and calcium oxide powder as mineralizing agents. The powder comprises the following components in percentage by weight: 60-95% of quartz glass powder, 1-30% of zircon powder, 0.5-5% of alumina powder and 0.1-5% of calcium carbonate powder. Paraffin, beeswax, polyethylene and polyethylene glycol are used as plasticizers for hot-press injection molding. The preparation method comprises the following steps: ball-milling and uniformly mixing the powder materials, putting the powder materials into a molten plasticizer for mixing, and carrying out hot-press injection molding on a ceramic core molding machine. A quartz glass rod/tube is pre-arranged in the position, corresponding to the thick and large section of the mold core, in the mold core mold before pressure injection, and the ceramic mold core formed through hot pressure injection molding is put into a box-type resistance furnace to be roasted after being trimmed and corrected. The silicon oxide-based ceramic core prepared by the invention has the characteristics of high high-temperature strength, good creep resistance, small firing shrinkage, stable size and high core removal efficiency.

Description

technical field [0001] The invention belongs to the field of high-temperature alloy directional solidification blade precision casting, relates to a large-size directional hollow blade part of a heavy-duty gas turbine, in particular to a silicon oxide-based ceramic core for directional solidification and a preparation method thereof. Background technique [0002] High-pressure turbine blades are important components of gas turbines. In order to continuously increase the gas inlet temperature before the turbine, countries around the world have developed from solid blades to hollow blades, from polycrystalline blades to the current directional and single crystal blades. The purpose is to continuously improve gas turbines. comprehensive performance. At present, the temperature of the front inlet of the advanced aero-engine turbine has reached 1757°C, and the temperature of the front inlet of the heavy-duty gas turbine turbine has also reached 1600°C, and the heavy-duty gas turb...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/14C04B35/622C04B35/626C04B35/64B22C9/10B22C1/00B22C1/02B22C1/08B22C9/04
CPCC04B35/14C04B35/622C04B35/626C04B35/64B22C9/10B22C1/00B22C1/02B22C1/08B22C9/04C04B2235/36C04B2235/3217C04B2235/442C04B2235/3244C04B2235/6562C04B2235/6567C04B2235/96
Inventor 刘孝福娄延春谢华生郭新力税国彦金磊关洋
Owner SHENYANG RES INST OF FOUNDRY
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