CN110735714B - Engine thermal protection structure and processing technology thereof - Google Patents
Engine thermal protection structure and processing technology thereof Download PDFInfo
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- CN110735714B CN110735714B CN201911006932.6A CN201911006932A CN110735714B CN 110735714 B CN110735714 B CN 110735714B CN 201911006932 A CN201911006932 A CN 201911006932A CN 110735714 B CN110735714 B CN 110735714B
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- carbon fiber
- thermal protection
- fiber bundles
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- temperature alloy
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K31/00—Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by only one of the preceding main groups
- B23K31/02—Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by only one of the preceding main groups relating to soldering or welding
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
Abstract
The invention relates to an engine thermal protection structure and a processing technology thereof, belonging to the technical field of structural thermal protection. The invention provides an engine thermal protection structure which is formed by implanting a high-temperature-resistant alloy framework, a loaded fuel oil cooling channel and an antioxidant C/SiC carbon fiber bundle into a composite high-temperature ceramic material. The active and passive cooling structures are compounded together, the oxidation-resistant C/SiC carbon fiber bundles are implanted into regular hexagonal angular point row holes on the high-temperature alloy framework, the carbon fiber bundles are further used as the framework, and a wet method or a dry method is adopted to fill high-temperature ceramic thermal barrier materials to form the anti-stripping and anti-falling thermal barrier coating, so that the thermal protection effect can be greatly improved by combining a thermal protection mode.
Description
Technical Field
The invention belongs to the technical field of structural thermal protection, and particularly relates to an engine thermal protection structure and a processing technology thereof.
Background
There are generally two approaches to thermal protection of certain engine structures: the first scheme is as follows: passive thermal protection, namely an engine prepared from a high-temperature-resistant composite material guarantees the structure and the function of the engine by utilizing the heat resistance of the engine; scheme II: the active heat protection scheme utilizes the heat absorption potential of the aircraft with fuel to cool and protect the structural material of the engine, and coats a high-temperature-resistant thermal barrier coating on the inner wall of the engine, so that the heat loss of a combustion chamber is reduced, the heat sink requirement on the fuel is reduced, and more effective protection is provided for the structure of the engine. The two schemes are typical of the current engine thermal protection, and have important practical significance.
The first scheme applied at present, namely the passive thermal protection scheme, has the disadvantages of high cost, short service life and low reusability. And the second scheme is that the thickness of a thermal barrier coating coated on the inner wall of the engine combustion chamber in the active fuel cooling scheme is difficult to increase, the thermal barrier coating is easy to crack and fall off, the reusability is low, and the like. Thus placing higher heat sink demands on actively cooled limited cooling fuels.
Disclosure of Invention
Technical problem to be solved
The technical problem to be solved by the invention is as follows: the engine thermal protection structure capable of improving the thermal protection effect is provided for solving the problems of thermal protection of the existing engine combustion chamber and the existing spray pipe.
(II) technical scheme
In order to solve the technical problem, the invention provides an engine thermal protection structure, which comprises a high-temperature alloy framework 6, wherein the high-temperature alloy framework 6 comprises a bottom and a bulge which is upwards grown on the bottom, a thermal protection structure panel 1 is welded above the bulge, and the welding surface is a contact surface of the bulge and the thermal protection structure panel 1; the protrusions of the high-temperature alloy skeleton 6 are arranged to form a plurality of equally spaced cooling fuel channels 2; in the space formed by the projections of the superalloy skeleton 6, the region other than the cooling fuel channel 2 is filled with an aerogel filler 3; uniformly arranging holes at angular points of a regular hexagon with the side length of 2mm-10mm at the bottom of the high-temperature alloy framework 6 and right below the aerogel filler 3, implanting antioxidant C/SiC carbon fiber bundles 5 into the holes, wherein one part of the C/SiC carbon fiber bundles 5 is positioned in the bottom of the high-temperature alloy framework 6, and the other part of the C/SiC carbon fiber bundles is exposed below the bottom of the high-temperature alloy framework 6; the method is characterized in that C/SiC carbon fiber bundles 5 are used as a framework, a wet method or a dry method is adopted, and a high-temperature ceramic thermal barrier material 4 is filled in a gap in the C/SiC carbon fiber bundles 5 at the bottom of a high-temperature alloy framework 6, a gap in the C/SiC carbon fiber bundles 5 exposed below the bottom and a gap between every two C/SiC carbon fiber bundles 5, so that the high-temperature ceramic thermal barrier material 4 and the C/SiC carbon fiber bundles 5 form a composite thermal barrier coating.
Preferably, the cooling fuel channel 2 has a cross-sectional area of 1.5mm2—20mm2The interface is rectangular, circular or elliptical.
Preferably, the material of the superalloy skeleton 6 is GH 3128.
Preferably, the C/SiC carbon fiber bundle 5 is a woven multi-strand gathered bundle, which is implanted after being sewn according to the diameter of the micropores.
Preferably, the aerogel filler 3 is made of high-temperature resistant aerogel with temperature resistance of not less than 1200 ℃, or is replaced by high-temperature foam alloy.
Preferably, the thermal protection structural panel 1 is a superalloy sheet with a thickness of 0.8-1.2 mm.
Preferably, the thickness h of the bottom is 0.8mm to 1.2 mm.
Preferably, the gap between every two C/SiC carbon fiber bundles 5 is opposite to the cooling fuel oil channel 2 and is positioned below the bottom of the high-temperature alloy framework 6.
Preferably, micropores with the diameter of 0.1 mm-1.0 mm are distributed on the bottom of the high-temperature alloy framework 6 and at the corner points of a regular hexagon with the side length of 2mm-10mm at the position right below the aerogel filler 3.
The invention also provides a processing technology of the engine thermal protection structure, which comprises the following steps: processing a high-temperature alloy framework 6, weaving an antioxidant C/SiC fiber bundle 5, filling an aerogel material 3, welding a thermal protection structure panel 1 on the top of the high-temperature alloy framework 6 to form a thermal protection structure, and finally completing the implantation of a high-temperature ceramic thermal barrier material 4 by adopting a wet method or a dry method.
(III) advantageous effects
The invention provides an engine thermal protection structure which is formed by implanting high-temperature-resistant alloy frameworks, a loaded fuel oil cooling channel and antioxidant C/SiC carbon fibers into a composite high-temperature ceramic material. The active and passive cooling structures are combined together, the oxidation-resistant C/SiC carbon fiber bundles are implanted into regular hexagonal corner row holes on the high-temperature alloy framework, the C/SiC carbon fiber bundles are further used as the framework, and the high-temperature ceramic thermal barrier material is filled by a wet method or a dry method to form the anti-stripping and anti-falling thermal barrier coating, so that the thermal protection effect can be greatly improved by combining the thermal protection mode.
Drawings
FIG. 1 is a cross-sectional view of the engine heat shield structure of the present invention;
FIG. 2 is a schematic view of a superalloy skeleton in the engine thermal shield structure of the present invention.
Detailed Description
In order to make the objects, contents, and advantages of the present invention clearer, the following detailed description of the embodiments of the present invention will be made in conjunction with the accompanying drawings and examples.
The invention provides an engine thermal protection structure, which comprises a high-temperature alloy framework 6, as shown in figures 1 and 2, the upper part of figure 2 is a sectional view of the high-temperature alloy framework 6, the high-temperature alloy framework 6 comprises a bottom and a bulge which grows upwards from the bottom, a thermal protection structure panel 1 is welded above the bulge, the welding surface is the contact surface of the bulge and the thermal protection structure panel 1, and the thickness h of the bottom is 0.8 mm-1.2 mm; the lower part of the figure 2 is a top plan view of a high-temperature alloy framework 6, the bulges of the high-temperature alloy framework 6 are arranged to form a plurality of equally spaced cooling fuel oil channels 2, aerogel fillers 3 are filled in the space formed by the bulges of the high-temperature alloy framework 6 except the cooling fuel oil channels 2, micropores with the diameter of 0.1 mm-1.0 mm are uniformly distributed at the corner points of a regular hexagon with the side length of 2mm-10mm at the position right below the positions where the aerogel fillers 3 are filled at the bottom of the high-temperature alloy framework 6, antioxidant C/SiC carbon fiber bundles 5 are implanted in the micropores, one part of the C/SiC carbon fiber bundles 5 is positioned in the bottom of the high-temperature alloy framework 6, and the other part of the C/SiC carbon fiber bundles is exposed below the bottom of the high-temperature alloy framework; then, the C/SiC carbon fiber bundles 5 are used as a framework, and a wet method or a dry method is adopted to fill gaps in the C/SiC carbon fiber bundles 5 at the bottom of the high-temperature alloy framework 6, gaps in the C/SiC carbon fiber bundles 5 exposed below the bottom and gaps between every two C/SiC carbon fiber bundles 5 (which are opposite to the cooling fuel oil channel 2 and are positioned below the bottom of the high-temperature alloy framework 6) with the high-temperature ceramic thermal barrier material 4, so that the high-temperature ceramic thermal barrier material 4 and the C/SiC carbon fiber bundles 5 form a cracking-resistant and falling-resistant composite thermal barrier coating;
wherein the cross-sectional area of the cooling fuel channel 2 is 1.5mm2—20mm2The interface is rectangular, circular or elliptical; high temperature alloyThe material of the framework 6 is GH 3128.
The C/SiC carbon fiber bundle 5 is a bundle formed by gathering woven multi-strand yarns, and is implanted after being sewn according to the diameter of the micropores in the figure 2;
the aerogel filler 3 is made of high-temperature resistant aerogel with the temperature resistance of not less than 1200 ℃, or is replaced by high-temperature foam alloy;
the thermal protection structure panel 1 (engine combustion chamber, nozzle shell) is a high-temperature alloy plate with the thickness of 0.8-1.2 mm;
the basic processing steps of the thermal protection structure of the invention are as follows: processing a high-temperature-resistant alloy framework material 6 according to the figure 2, compositely weaving and compiling an antioxidant C/SiC fiber bundle 5, filling an aerogel material 3, welding a thermal protection structure panel 1 at the top of a channel to form a thermal protection structure, and finally completing the implantation of a high-temperature ceramic thermal barrier material 4 by adopting a wet method or a dry method.
The invention arranges a right hexagonal corner position on a high-temperature-resistant alloy framework as a fiber bundle hole for implanting an antioxidant C/SiC carbon fiber bundle, and a high-temperature ceramic thermal barrier material is loaded on the high-temperature-resistant alloy framework by taking the fiber bundle as the framework to form a cracking-resistant and falling-resistant composite thermal barrier material; the special regular hexagonal corner implantation structure improves the crack resistance of the thermal barrier ceramic material, reduces the toughness requirement on the high-temperature ceramic thermal barrier material, greatly prolongs the service life and meets the full-use requirement; the thickening of the high-temperature ceramic thermal barrier material greatly increases the temperature gradient and reduces the demand of the structure on fuel heat sink; the utilization of the composite thermal barrier material reduces the consumption of high-density high-temperature-resistant alloy skeleton (steel) materials, and the structural weight is greatly reduced; the invention can greatly improve the thickness of the thermal barrier coating material on the inner surface of the spray pipe of the combustion chamber from the current thickness of less than 1.0mm to 1.0 mm-10mm, even higher.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (10)
1. The thermal protection structure of the engine is characterized by comprising a high-temperature alloy framework (6), wherein the high-temperature alloy framework (6) comprises a bottom and a bulge growing upwards at the bottom, a thermal protection structure panel (1) is welded above the bulge, and the welding surface is the contact surface of the bulge and the thermal protection structure panel (1); the protrusions of the high-temperature alloy skeleton (6) are arranged to form a plurality of equally spaced cooling fuel channels (2); filling aerogel fillers (3) in the space formed by the bulges of the high-temperature alloy skeleton (6) except for the cooling fuel channel (2); micropores are uniformly distributed at the corner points of a regular hexagon at the bottom of the high-temperature alloy framework (6) and right below the aerogel filler (3), antioxidant C/SiC carbon fiber bundles (5) are implanted into the micropores, one part of the C/SiC carbon fiber bundles (5) is positioned in the bottom of the high-temperature alloy framework (6), and the other part of the C/SiC carbon fiber bundles is exposed below the bottom of the high-temperature alloy framework (6); the method is characterized in that C/SiC carbon fiber bundles (5) are used as a framework, a wet method or a dry method is adopted, and a high-temperature ceramic thermal barrier material (4) is filled in a gap in the C/SiC carbon fiber bundles (5) at the bottom of a high-temperature alloy framework (6), the gap in the C/SiC carbon fiber bundles (5) exposed below the bottom and a gap between every two C/SiC carbon fiber bundles (5), so that the high-temperature ceramic thermal barrier material (4) and the C/SiC carbon fiber bundles (5) form a composite thermal barrier coating.
2. A structure as claimed in claim 1, characterized in that the cross-sectional area of the cooling fuel channel (2) is 1.5mm2—20mm2The cross section is rectangular, circular or elliptical.
3. A structure according to claim 2, characterized in that the material of the superalloy skeleton (6) is GH 3128.
4. A structure as claimed in claim 3, characterized in that said C/SiC carbon fiber bundle (5) is a woven multi-strand gathered bundle, sewn at a micropore diameter and implanted.
5. Structure as claimed in claim 4, characterized in that said aerogel pack (3) is replaced by a refractory aerogel, resistant to temperatures not lower than 1200 ℃, or by a refractory foam alloy.
6. A structure as claimed in claim 5, characterized in that said thermal protection structural panel (1) is a superalloy sheet with a thickness of 0.8-1.2 mm.
7. The structure of claim 6, wherein the thickness h of the base is 0.8mm to 1.2 mm.
8. The structure according to claim 1, characterized in that the space between each two C/SiC carbon fiber bundles (5) is located opposite the cooling fuel channel (2) below the bottom of the superalloy skeleton (6).
9. The structure according to claim 7, characterized in that the micropores with a pore diameter of 0.1mm to 1.0mm are uniformly distributed at the corner points of a 2mm to 10mm side regular hexagon at the bottom of the superalloy skeleton (6) at a position directly below the aerogel filler (3).
10. A process for manufacturing an engine heat shield structure according to any one of claims 1 to 9, comprising the steps of: processing a high-temperature alloy framework (6), weaving an antioxidant C/SiC fiber bundle (5), filling an aerogel material (3), welding a thermal protection structure panel (1) on the top of the high-temperature alloy framework (6) to form a thermal protection structure, and finally completing the implantation of a high-temperature ceramic thermal barrier material (4) by adopting a wet method or a dry method.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911006932.6A CN110735714B (en) | 2019-10-22 | 2019-10-22 | Engine thermal protection structure and processing technology thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911006932.6A CN110735714B (en) | 2019-10-22 | 2019-10-22 | Engine thermal protection structure and processing technology thereof |
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| Publication Number | Publication Date |
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| CN110735714A CN110735714A (en) | 2020-01-31 |
| CN110735714B true CN110735714B (en) | 2020-07-17 |
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| CN112829387A (en) * | 2021-02-26 | 2021-05-25 | 彩虹无人机科技有限公司 | Sound-absorbing tile attached to outer surface of underwater vehicle shell and underwater vehicle |
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| US6389801B1 (en) * | 1998-12-17 | 2002-05-21 | Daimlerchrysler Ag | Jet propulsion power unit with non-metal components |
| US7785076B2 (en) * | 2005-08-30 | 2010-08-31 | Siemens Energy, Inc. | Refractory component with ceramic matrix composite skeleton |
| CN103723269A (en) * | 2013-09-11 | 2014-04-16 | 太仓派欧技术咨询服务有限公司 | Thermal protection structure |
| US10100666B2 (en) * | 2013-03-29 | 2018-10-16 | General Electric Company | Hot gas path component for turbine system |
| CN110056432A (en) * | 2018-01-18 | 2019-07-26 | 通用电气公司 | The thermoplastic pipe and component of Thermal protection |
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2019
- 2019-10-22 CN CN201911006932.6A patent/CN110735714B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6389801B1 (en) * | 1998-12-17 | 2002-05-21 | Daimlerchrysler Ag | Jet propulsion power unit with non-metal components |
| US7785076B2 (en) * | 2005-08-30 | 2010-08-31 | Siemens Energy, Inc. | Refractory component with ceramic matrix composite skeleton |
| US10100666B2 (en) * | 2013-03-29 | 2018-10-16 | General Electric Company | Hot gas path component for turbine system |
| CN103723269A (en) * | 2013-09-11 | 2014-04-16 | 太仓派欧技术咨询服务有限公司 | Thermal protection structure |
| CN110056432A (en) * | 2018-01-18 | 2019-07-26 | 通用电气公司 | The thermoplastic pipe and component of Thermal protection |
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| "热防护设计分析技术发展中的新概念与新趋势";杨强等;《航空学报》;20150925;第36卷(第9期);2981-2991 * |
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