CN116045308A - Light active and passive composite cooling combustion chamber based on high-temperature-resistant composite material - Google Patents
Light active and passive composite cooling combustion chamber based on high-temperature-resistant composite material Download PDFInfo
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- CN116045308A CN116045308A CN202310036079.2A CN202310036079A CN116045308A CN 116045308 A CN116045308 A CN 116045308A CN 202310036079 A CN202310036079 A CN 202310036079A CN 116045308 A CN116045308 A CN 116045308A
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- Prior art keywords
- cooling
- composite material
- coolant
- liquid collecting
- cylinder body
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- 238000001816 cooling Methods 0.000 title claims abstract description 102
- 239000002131 composite material Substances 0.000 title claims abstract description 38
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 23
- 239000002826 coolant Substances 0.000 claims abstract description 35
- 239000007788 liquid Substances 0.000 claims abstract description 33
- 229910000838 Al alloy Inorganic materials 0.000 claims abstract description 27
- UQZIWOQVLUASCR-UHFFFAOYSA-N alumane;titanium Chemical compound [AlH3].[Ti] UQZIWOQVLUASCR-UHFFFAOYSA-N 0.000 claims abstract description 27
- 239000000463 material Substances 0.000 claims abstract description 23
- 239000011153 ceramic matrix composite Substances 0.000 claims abstract description 12
- 230000001172 regenerating effect Effects 0.000 description 9
- 238000005516 engineering process Methods 0.000 description 5
- 239000007789 gas Substances 0.000 description 5
- 239000000446 fuel Substances 0.000 description 3
- 230000008929 regeneration Effects 0.000 description 3
- 238000011069 regeneration method Methods 0.000 description 3
- 230000008646 thermal stress Effects 0.000 description 3
- 238000002679 ablation Methods 0.000 description 2
- 230000004907 flux Effects 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000035900 sweating Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/18—Composite ram-jet/rocket engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
Abstract
The invention discloses a light active and passive composite cooling combustion chamber based on a high-temperature resistant composite material, which comprises an inner cylinder and an outer cylinder, wherein the inner cylinder is made of a high-temperature ceramic matrix composite material, and the outer cylinder is made of a gradient C/C composite material; two titanium aluminum alloy cooling structures are symmetrically sleeved outside the outer cylinder, each titanium aluminum alloy cooling structure comprises a semicircular cooling cylinder body, a plurality of cooling channels are circumferentially arranged on the cylinder wall of the cooling cylinder body and related to the axis of the cooling cylinder body, the extending direction of each cooling channel is the same as the axis direction of the cooling cylinder body, liquid collecting cavities are arranged at two ends of the cooling cylinder body, and each liquid collecting cavity is communicated with the end part of each cooling channel located at the same side; each liquid collecting cavity is communicated with a pipe connecting opening; one of the pipe connecting ports is used for introducing a coolant and filling the coolant into a liquid collecting cavity communicated with the coolant; each cooling channel is used for the coolant to flow through and absorb heat and finally reach the other liquid collecting cavity; and the other pipe connecting port is used for flowing out the coolant.
Description
Technical Field
The invention belongs to the technical field of heat protection of scramjet engines or combined power engines, and particularly relates to a light active and passive composite cooling combustion chamber based on a high-temperature-resistant composite material.
Background
The rocket-based ramjet combined cycle (RBCC) engine is a novel combined power form combining a rocket engine and a ramjet engine, so that the RBCC engine combines the advantages of high thrust-weight ratio of the rocket engine and high specific impulse of the ramjet engine, and further the aircraft can realize wide-range speed adjustment from zero-speed take-off to high Mach number flight, thereby greatly improving task adaptability and having great development potential in future near-ground air-day transportation.
RBCC engines fall into four modes: the jet mode, the sub-combustion stamping mode, the scramjet stamping mode and the rocket mode, wherein the air suction type engine works in the first three modes, and the highest Mach number in flight in the air suction state can exceed Ma7 due to the wide range of the working speed range of the engine, and the total temperature of incoming flow can be ultrahigh by 2000K; in the combustion chamber of the ramjet engine, fuel and incoming air which obtains deceleration and pressurization enter the combustion chamber and are mixed and combusted, chemical energy of the fuel is converted to work, and the temperature of high-temperature fuel gas in the combustion chamber of the ramjet engine can reach about 2900K currently. It follows that RBCC engines need to operate in opposition to dual heat loads from both high Wen Lailiu and high temperature combustion gases, which place high demands on the engine's thermal protection technology.
The thermal protection technology currently used in engines can be divided into passive thermal protection and active thermal protection. In passive heat protection, the existing material cannot be directly used for a plurality of times in such a high heat environment, and the heat insulation layer ablation cooling technology is only suitable for short-time single heat protection due to the limitation of the thickness of an ablation layer. In active heat protection, the heat protection capability of the incoming air used for film cooling cannot be further improved due to the high temperature of the incoming air, and liquid film cooling, sweating cooling and regenerative cooling using engine fuel as a coolant have limited total heat sinking available for cooling due to the limitation of the combustion equivalence ratio of the engine, and meanwhile, an active cooling system can increase the dry weight of the engine and affect the overall performance of an aircraft. Therefore, the combustion chamber thermal protection technology is one of the key technologies of RBCC engines.
Disclosure of Invention
The invention aims to provide a light active and passive composite cooling combustion chamber based on a high-temperature-resistant composite material, so as to solve the problems of limited temperature resistance of a combustion chamber wall material of an existing RBCC ramjet engine, insufficient heat sink of a coolant and high structural quality of an engine using an active cooling system.
The invention adopts the following technical scheme: a light active and passive composite cooling combustion chamber based on a high-temperature-resistant composite material comprises an inner cylinder and an outer cylinder which are coaxially sleeved inside and outside, wherein the inner cylinder is made of a high-temperature ceramic matrix composite material, and the outer cylinder is made of a gradient C/C composite material; two titanium aluminum alloy cooling structures are symmetrically sleeved outside the outer cylinder, each titanium aluminum alloy cooling structure comprises a semicircular cooling cylinder body, a plurality of cooling channels are circumferentially arranged on the cylinder wall of the cooling cylinder body and related to the axis of the cooling cylinder body, the extending direction of each cooling channel is the same as the axis direction of the cooling cylinder body, liquid collecting cavities are arranged at two ends of the cooling cylinder body, and each liquid collecting cavity is communicated with the end part of each cooling channel located at the same side; each liquid collecting cavity is communicated with a pipe connecting opening;
one of the pipe connecting ports is used for introducing a coolant and filling the coolant into a liquid collecting cavity communicated with the coolant; each cooling channel is used for the coolant to flow through and absorb heat and finally reach the other liquid collecting cavity; and the other pipe connecting port is used for flowing out the coolant.
Further, two sides of the two titanium aluminum alloy cooling structures are detachably connected through side flanges.
Further, both ends of the outer cylinder, the inner cylinder and the two titanium aluminum alloy cooling structures are connected with round flanges.
Further, each cooling channel has a rectangular cross section.
The beneficial effects of the invention are as follows:
(1) The high-temperature ceramic matrix composite is used as a hot wall surface material of a high-temperature gas field, so that the highest allowable temperature of a combustion chamber of the engine is improved;
(2) The titanium-aluminum alloy with lower density is used as a regenerative cooling structure material, so that the temperature resistance is ensured and the structural quality of the engine is reduced;
(3) The gradient C/C composite material is used for connecting the high-temperature ceramic matrix composite material and the titanium aluminum alloy regeneration cooling structure, so that the problem of heat matching caused by the difference of thermal expansion coefficients under the high-temperature condition is solved, and heat transfer is blocked;
(4) Two titanium-aluminum alloy regeneration cooling structures are used for corresponding to the two groups of liquid collecting cavities and the liquid receiving ports, so that the flow distribution of the coolant in the cooling channel is more uniform, the whole engine structure is uniformly cooled, the structural thermal stress is reduced, and the cooling efficiency of the coolant is improved;
(5) The heat flux density at the cooling channel is reduced through the multi-layer material structure, the heat sink use of the coolant is reduced, and the use of the coolant is further saved.
Drawings
FIG. 1 is a schematic perspective view of a light active and passive composite cooling combustion chamber based on a high temperature resistant composite material;
FIG. 2 is a schematic cross-sectional view of FIG. 1 along a direction of parallel air flow;
FIG. 3 is a schematic cross-sectional view of the middle of FIG. 1 taken along the direction of the incoming air flow;
FIG. 4 is an enlarged schematic view of FIG. 2 at A;
fig. 5 is an enlarged schematic view at B in fig. 3.
Wherein, 1. Cooling channel; 2. a liquid collection cavity; 3. a pipe connecting port; 4. a circular flange; 5. a side flange; 6. an inner cylinder; 7. an outer cylinder; 8. and cooling the cylinder.
Detailed Description
The invention will be described in detail below with reference to the drawings and the detailed description.
The invention provides a light active and passive composite cooling combustion chamber based on a high-temperature-resistant composite material, which is shown in figures 1 to 5 and comprises an outer cylinder 7 and an inner cylinder 6 which are coaxially sleeved inside and outside, wherein the inner cylinder 6 is made of a high-temperature ceramic matrix composite material, and the outer cylinder 7 is made of a gradient C/C composite material. The gradient C/C composite material is a composite material with gradient change characteristics of heat conductivity coefficient along a certain direction, wherein the heat conductivity coefficient of the composite material is smaller at one side close to the high-temperature ceramic matrix composite material and the heat conductivity coefficient of the composite material is larger at one side close to the metal, so that the heat conductivity coefficient difference of the materials at two sides is balanced to solve the problem of high-temperature heat matching.
Two titanium-aluminum alloy cooling structures are symmetrically sleeved outside the outer cylinder 7, each titanium-aluminum alloy cooling structure comprises a semicircular cooling cylinder body 8, a plurality of cooling channels 1 are circumferentially arranged on the cylinder wall of the cooling cylinder body 8 around the axis of the cooling cylinder body 8, the extending direction of each cooling channel 1 is the same as the axis direction of the cooling cylinder body 8, liquid collecting cavities 2 are respectively arranged at two ends of the cooling cylinder body 8, and each liquid collecting cavity 2 is communicated with the end part of each cooling channel 1 on the same side; each liquid collecting cavity 2 is communicated with a connecting pipe port 3. One of the connecting ports 3 is used for introducing a coolant and filling the liquid collecting cavity 2 communicated with the coolant; each cooling channel 1 is used for the coolant to flow through and absorb heat and finally reach the other liquid collecting cavity 2; the other of the connection openings 3 is used for the outflow of the coolant.
Both ends of the cooling channel 8 are respectively communicated with liquid collecting cavities 2 at both ends, and each liquid collecting cavity 2 is provided with a connecting pipe port 3. Two titanium-aluminum alloy regeneration cooling structures are used for corresponding to the two groups of liquid collecting cavities and the pipe connecting ports, so that the flow distribution of the coolant in the cooling channel is more uniform, the whole engine structure is uniformly cooled, the structural thermal stress is reduced, and the cooling efficiency of the coolant is improved.
The invention uses an inner cylinder 6 made of a high-temperature ceramic matrix composite material as a structure which is in direct contact with a high-temperature gas field, an outer cylinder 7 made of a gradient C/C composite material is wrapped outside the inner cylinder 6 as a high-temperature heat matching transition layer, and the outermost layer is two titanium-aluminum alloy cooling structures symmetrically arranged along the flow field. The high-temperature ceramic matrix composite is used as a hot wall surface material of a high-temperature gas field, so that the highest allowable temperature of a combustion chamber of the engine can be improved; the titanium aluminum alloy with lower density is used as a regenerative cooling structure material, so that the temperature resistance can be ensured, and the structural quality of the engine can be reduced. The gradient C/C composite material is used for connecting the high-temperature ceramic matrix composite material and the titanium-aluminum alloy regenerative cooling structure, so that the problem of heat matching caused by the difference of thermal expansion coefficients under the high-temperature condition is solved, and heat transfer is blocked.
In some embodiments, two sides of the titanium-aluminum alloy cooling structure are detachably connected through side flanges 5. The inner cylinder 6 and the outer cylinder 7 are fixed by applying pretightening force while being connected, thereby forming an integral multi-layer regenerative cooling heat exchange structure. The tight contact of the multi-layer materials is ensured while the assembly and the disassembly are convenient, and the difference of the thermal expansion deformation of the inner layer material and the outer layer material at high temperature is counteracted by pre-tightening.
In some embodiments, the outer cylinder 7, the inner cylinder 6 and both ends of the two titanium aluminum alloy cooling structures are connected with circular flanges 4. The structure is mounted in the RBCC engine by a circular flange 4, connected to other structural components.
In some embodiments, inside each titanium-aluminum alloy cooling structure, as shown in fig. 5, the cooling channels 8 uniformly distributed along the air inflow direction have a rectangular cross section. The processing complexity is reduced, the heat exchange efficiency of the active cooling structure is improved, and the occurrence of a local high-temperature area on the metal hot wall surface is avoided as much as possible.
The working process of the light active and passive composite cooling combustion chamber based on the high-temperature-resistant composite material provided by the invention is as follows: in use, coolant enters the connecting pipe port 3 on one side of the titanium-aluminum alloy cooling structure through an external supply system and flows in the liquid collecting cavity 2 communicated with the connecting pipe port, and after the liquid collecting cavity 2 is filled with the coolant, the coolant enters a series of parallel cooling channels 8 connected with the liquid collecting cavity 2. The coolant absorbs heat conducted from the high-temperature gas field in the cooling channel 8, the temperature rises, and then enters the liquid collecting cavity 2 on the other side of the titanium-aluminum alloy cooling structure, the coolant is collected at the liquid collecting cavity, and finally flows out from the connecting pipe port 3 of the liquid collecting cavity 2, so that the whole regenerative cooling heat exchange process is completed.
The invention uses the high-temperature ceramic matrix composite as the hot wall surface material of the high-temperature gas field, thereby improving the highest allowable temperature of the combustion chamber of the engine; the titanium aluminum alloy with lower density is used as a regenerative cooling structure material, so that the temperature resistance is ensured, and the structural quality of the engine is reduced; the gradient C/C composite material is used for connecting the high-temperature ceramic matrix composite material and the titanium-aluminum alloy regenerative cooling structure, so that the problem of heat matching caused by the difference of thermal expansion coefficients under the high-temperature condition is solved, and heat transfer is blocked; the two titanium-aluminum alloy regenerative cooling structures correspond to the two groups of liquid collecting cavities and the pipe connecting ports, so that the flow distribution of the coolant in the cooling channel is more uniform, the whole engine structure is uniformly cooled, the structural thermal stress is reduced, and the cooling efficiency of the coolant is improved; the heat flux density at the cooling channel is reduced through the multi-layer material structure, the heat sink use of the coolant is reduced, and the use of the coolant is further saved.
Claims (4)
1. The light active and passive composite cooling combustion chamber based on the high-temperature-resistant composite material is characterized by comprising an inner cylinder (6) and an outer cylinder (7) which are coaxially sleeved inside and outside, wherein the inner cylinder (6) is made of a high-temperature ceramic matrix composite material, and the outer cylinder (7) is made of a gradient C/C composite material; two titanium aluminum alloy cooling structures are symmetrically sleeved outside the outer cylinder (7), each titanium aluminum alloy cooling structure comprises a semicircular cooling cylinder body (8), a plurality of cooling channels (1) are circumferentially arranged on the cylinder wall of the cooling cylinder body (8) relative to the axis of the cooling cylinder body (8), the extending direction of each cooling channel (1) is the same as the axis direction of the cooling cylinder body (8), liquid collecting cavities (2) are respectively arranged at two ends of the cooling cylinder body (8), and each liquid collecting cavity (2) is communicated with the end part of each cooling channel (1) located at the same side; each liquid collecting cavity (2) is communicated with one pipe connecting opening (3);
one of the connecting ports (3) is used for introducing a coolant and filling the liquid collecting cavity (2) communicated with the coolant; -each of said cooling channels (1) for the coolant to flow through and absorb heat, eventually reaching the other of said liquid-collecting cavities (2); the other connecting pipe port (3) is used for the outflow of the coolant.
2. A lightweight active and passive composite cooling combustion chamber based on high temperature resistant composite material as claimed in claim 1, wherein two sides of the two titanium aluminum alloy cooling structures are detachably connected by side flanges (5).
3. The light active and passive composite cooling combustion chamber based on the high-temperature resistant composite material as claimed in claim 1, wherein the two ends of the outer cylinder (7), the inner cylinder (6) and the two titanium aluminum alloy cooling structures are connected with round flanges (4).
4. A lightweight active and passive composite cooled combustion chamber based on a high temperature resistant composite material as in claim 1, wherein each of said cooling channels (8) is rectangular in cross section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310036079.2A CN116045308A (en) | 2023-01-10 | 2023-01-10 | Light active and passive composite cooling combustion chamber based on high-temperature-resistant composite material |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310036079.2A CN116045308A (en) | 2023-01-10 | 2023-01-10 | Light active and passive composite cooling combustion chamber based on high-temperature-resistant composite material |
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| Publication Number | Publication Date |
|---|---|
| CN116045308A true CN116045308A (en) | 2023-05-02 |
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| CN202310036079.2A Pending CN116045308A (en) | 2023-01-10 | 2023-01-10 | Light active and passive composite cooling combustion chamber based on high-temperature-resistant composite material |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118361751A (en) * | 2024-06-19 | 2024-07-19 | 西北工业大学 | Nested composite light high-temperature-resistant regenerative cooling combustion chamber |
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| CN115419918A (en) * | 2022-09-21 | 2022-12-02 | 哈尔滨工业大学 | High-speed combustion chamber heat-proof and drag-reduction structure based on steam reforming sweating cooling |
| CN218151177U (en) * | 2022-10-17 | 2022-12-27 | 陕西空天动力研究院有限公司 | Integrated thrust chamber with thermal protection structure |
-
2023
- 2023-01-10 CN CN202310036079.2A patent/CN116045308A/en active Pending
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| KR20060077002A (en) * | 2004-12-29 | 2006-07-05 | 한국항공우주연구원 | A combustor chamber with regenerative cooling for high-pressure liquid rocket engine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN118361751A (en) * | 2024-06-19 | 2024-07-19 | 西北工业大学 | Nested composite light high-temperature-resistant regenerative cooling combustion chamber |
| CN118361751B (en) * | 2024-06-19 | 2024-10-25 | 西北工业大学 | Nested composite light high-temperature-resistant regenerative cooling combustion chamber |
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