CN104451306A - Bearing seat for gas turbine - Google Patents
Bearing seat for gas turbine Download PDFInfo
- Publication number
- CN104451306A CN104451306A CN201410829346.2A CN201410829346A CN104451306A CN 104451306 A CN104451306 A CN 104451306A CN 201410829346 A CN201410829346 A CN 201410829346A CN 104451306 A CN104451306 A CN 104451306A
- Authority
- CN
- China
- Prior art keywords
- alloy
- bearing seat
- gas turbine
- preheating
- alloy material
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Landscapes
- Extrusion Of Metal (AREA)
Abstract
The invention discloses a bearing seat for a gas turbine. The bearing seat for the gas turbine comprises a metal body which is prepared from an alloy material; the alloy material is prepared from the following components in percentage by weight: 3.97% of Al, 4.25% of Pb, 6.77% of V, 1.29% of C, 6.65% of Ta, and the balance of Mg and inevitable impurities; the alloy material is prepared by the steps of 1) preheating Mg, Mg-Al alloy, Mg-Pb alloy, Mg-V alloy, Mg-C alloy and Mg-Ta alloy for 40min under a temperature of 223 DEG C; 2) charging protective gas into a smelting furnace, feeding preheated Mg, and then heating to smelt Mg; 3) feeding preheated Mg-Al alloy, Mg-Pb alloy, Mg-V alloy, Mg-C alloy and Mg-Ta alloy, and heating to fully smelt; 4) standing the melt and cooling to reach the temperature of 553 DEG C, and casting to obtain the alloy material. The bearing seat for the gas turbine is outstanding in resistance to friction, high temperature, corrosion and weather, and high in strength.
Description
Technical field
The present invention relates to internal combustion turbine bearing support.
Background technology
Internal combustion turbine is the generating set of widespread use, the environment for use more complicated of internal combustion turbine, all higher to the requirement of the abrasion-resistant of all parts of internal combustion turbine, high temperature resistant, corrosion-resistant, weather resistance and intensity.
Summary of the invention
The object of the present invention is to provide a kind of internal combustion turbine bearing support, it has excellent abrasion-resistant, high temperature resistant, corrosion-resistant, weather resistance and intensity.
For achieving the above object, technical scheme of the present invention is a kind of internal combustion turbine bearing support of design, and comprise metal master, described metal master is made up of alloy material, and by weight percentage, the composition of this alloy material is:
Al：3.97％，
Pb：4.25％，
V：6.77％，
C：1.29％，
Ta：6.65％，
Surplus is Mg and inevitable impurity;
Described alloy material is prepared as follows:
1) at 223 DEG C, by Mg, Mg-Al alloy, Mg-Pb alloy, Mg-V alloy, Mg-C alloy and Mg-Ta alloy preheating 40min;
2) pass into protective atmosphere in smelting furnace, drop into the Mg after preheating, and heating makes Mg melt;
3) Mg-Al alloy, Mg-Pb alloy, Mg-V alloy, Mg-C alloy and Mg-Ta alloy after dropping into preheating, heat up and fully melt;
4) be cooled to 553 DEG C by standing for melt body, die casting obtains alloy material.
Advantage of the present invention and beneficial effect are: provide a kind of internal combustion turbine bearing support, and it has excellent abrasion-resistant, high temperature resistant, corrosion-resistant, weather resistance and intensity.
Embodiment
Below in conjunction with embodiment, the specific embodiment of the present invention is further described.Following examples only for technical scheme of the present invention is clearly described, and can not limit the scope of the invention with this.
The technical scheme that the present invention specifically implements is:
A kind of internal combustion turbine bearing support, comprise metal master, described metal master is made up of alloy material, and by weight percentage, the composition of this alloy material is:
Al：3.97％，
Pb：4.25％，
V：6.77％，
C：1.29％，
Ta：6.65％，
Surplus is Mg and inevitable impurity;
Described alloy material is prepared as follows:
1) at 223 DEG C, by Mg, Mg-Al alloy, Mg-Pb alloy, Mg-V alloy, Mg-C alloy and Mg-Ta alloy preheating 40min;
2) pass into protective atmosphere in smelting furnace, drop into the Mg after preheating, and heating makes Mg melt;
3) Mg-Al alloy, Mg-Pb alloy, Mg-V alloy, Mg-C alloy and Mg-Ta alloy after dropping into preheating, heat up and fully melt;
4) be cooled to 553 DEG C by standing for melt body, die casting obtains alloy material.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the prerequisite not departing from the technology of the present invention principle; can also make some improvements and modifications, these improvements and modifications also should be considered as protection scope of the present invention.
Claims (1)
1. internal combustion turbine bearing support, is characterized in that, comprises metal master, and described metal master is made up of alloy material, and by weight percentage, the composition of this alloy material is:
Al：3.97％，
Pb：4.25％，
V：6.77％，
C：1.29％，
Ta：6.65％，
Surplus is Mg and inevitable impurity;
Described alloy material is prepared as follows:
1) at 223 DEG C, by Mg, Mg-Al alloy, Mg-Pb alloy, Mg-V alloy, Mg-C alloy and Mg-Ta alloy preheating 40min;
2) pass into protective atmosphere in smelting furnace, drop into the Mg after preheating, and heating makes Mg melt;
3) Mg-Al alloy, Mg-Pb alloy, Mg-V alloy, Mg-C alloy and Mg-Ta alloy after dropping into preheating, heat up and fully melt;
4) be cooled to 553 DEG C by standing for melt body, die casting obtains alloy material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410829346.2A CN104451306A (en) | 2014-12-23 | 2014-12-23 | Bearing seat for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410829346.2A CN104451306A (en) | 2014-12-23 | 2014-12-23 | Bearing seat for gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104451306A true CN104451306A (en) | 2015-03-25 |
Family
ID=52898046
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410829346.2A Pending CN104451306A (en) | 2014-12-23 | 2014-12-23 | Bearing seat for gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104451306A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB596102A (en) * | 1945-07-19 | 1947-12-29 | Rupert Martin Bradbury | A new magnesium base alloy |
| US4134759A (en) * | 1976-09-01 | 1979-01-16 | The Research Institute For Iron, Steel And Other Metals Of The Tohoku University | Light metal matrix composite materials reinforced with silicon carbide fibers |
| CN101440449A (en) * | 2008-12-23 | 2009-05-27 | 重庆大学 | Multicomponent heat resisting magnesium alloy and preparation thereof |
| CN101572851A (en) * | 2008-04-29 | 2009-11-04 | 沈阳航空工业学院 | Magnesium alloy integrally cast sound box and manufacturing method thereof |
| CN101575683A (en) * | 2009-06-01 | 2009-11-11 | 中国兵器工业第五二研究所 | High strength corrosion resistant rare earth cast magnesium alloy and preparation method thereof |
-
2014
- 2014-12-23 CN CN201410829346.2A patent/CN104451306A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB596102A (en) * | 1945-07-19 | 1947-12-29 | Rupert Martin Bradbury | A new magnesium base alloy |
| US4134759A (en) * | 1976-09-01 | 1979-01-16 | The Research Institute For Iron, Steel And Other Metals Of The Tohoku University | Light metal matrix composite materials reinforced with silicon carbide fibers |
| CN101572851A (en) * | 2008-04-29 | 2009-11-04 | 沈阳航空工业学院 | Magnesium alloy integrally cast sound box and manufacturing method thereof |
| CN101440449A (en) * | 2008-12-23 | 2009-05-27 | 重庆大学 | Multicomponent heat resisting magnesium alloy and preparation thereof |
| CN101575683A (en) * | 2009-06-01 | 2009-11-11 | 中国兵器工业第五二研究所 | High strength corrosion resistant rare earth cast magnesium alloy and preparation method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104451257A (en) | Double-fed wind driven generator seat | |
| CN104404301B (en) | Wind-driven generator directly drives dead axle | |
| CN104404302A (en) | Direct-driven rotor mechanism of wind turbine generator set | |
| CN104404303A (en) | Direct-drive rotating shaft for wind-driven generator | |
| CN104455943A (en) | Anti-explosion gas turbine housing | |
| CN104451305A (en) | Compressor bearing seat of gas turbine | |
| CN104451307A (en) | Housing of gas turbine | |
| CN104451308A (en) | Outer frame of gas engine | |
| CN104451306A (en) | Bearing seat for gas turbine | |
| CN104388755A (en) | Wind generator stator frame | |
| CN104451309A (en) | Outer stand of 15-gigawatt air cooling steam turbine | |
| CN104454029A (en) | Combustion gas turbine power turbine guide blade | |
| CN104454040A (en) | 350,000 KW air-cooling steam turbine internal machine base | |
| CN104451258A (en) | Wind driven generator stator | |
| CN104451315A (en) | Inner frame of gas turbine | |
| CN104632409A (en) | Low-pressure inner air cylinder of gas turbine | |
| CN105349912A (en) | Bearing seat for combustion turbine | |
| CN105543643A (en) | Outer machine base of gas turbine | |
| CN104404304A (en) | Wind-driven generator rotor | |
| CN105441812A (en) | Internal engine base of gas turbine | |
| CN105400996A (en) | Titanium tube | |
| CN105369141A (en) | Gas compressor bearing block of gas turbine | |
| CN105568181A (en) | Wind generating set cabin seat | |
| CN105543692A (en) | Housing of gas turbine | |
| CN105543650A (en) | Outer turbine base of 150000 KW air-cooling steam turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150325 |
|
| RJ01 | Rejection of invention patent application after publication |