CN110645117A - Ceramic thrust chamber for monopropellant hydroxyl nitrate amino thruster - Google Patents
Ceramic thrust chamber for monopropellant hydroxyl nitrate amino thruster Download PDFInfo
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- CN110645117A CN110645117A CN201910883269.1A CN201910883269A CN110645117A CN 110645117 A CN110645117 A CN 110645117A CN 201910883269 A CN201910883269 A CN 201910883269A CN 110645117 A CN110645117 A CN 110645117A
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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
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
Abstract
The invention discloses a ceramic thrust chamber for a monopropellant hydroxyl nitrate amino thruster, which comprises: placing steps, a catalytic front bed, a catalytic middle bed, a catalytic rear bed, a double-arc spray pipe, a front bed baffle, a middle bed baffle and a rear bed baffle; the left end face of the placing step is connected with an external sealing gasket, and the right end face of the placing step is movably connected with an external injector; the right end surface of the catalytic forebed is connected with the lower end surface of the forebed baffle; the right end face of the catalytic middle bed is connected with the lower end face of the middle bed baffle; the right end surface of the catalytic rear bed is connected with the lower end surface of the rear bed baffle. The invention solves the requirement of the hydroxylamine nitrate based thruster on an integrated high-temperature-resistant oxidation-resistant light thrust chamber.
Description
Technical Field
The invention belongs to the field of single-component catalytic decomposition thrusters of liquid rocket engines, and particularly relates to a ceramic thrust chamber for a single-component hydroxylamino nitrate thruster.
Background
For hydroxylamine nitrate (HAN) propulsion system design, the overhigh adiabatic combustion temperature of an engine is one of key problems needing to be solved, meanwhile, a great part of products of HAN combustion have strong oxidizing property and bring great harm to materials of a combustion chamber, and materials such as high-temperature alloy and the like lack sufficient strength at high temperature. At present, a single-component hydrazine engine generally adopts nickel-based high-temperature alloy as a spray pipe material. The nickel-based superalloy has limited temperature resistance, the maximum combustion temperature of an engine is generally limited by long-term reliable work, and the temperature of the nickel-based superalloy does not exceed 1100 ℃ for long-term work and is limited to 1200 ℃. Because of the temperature resistance limit of the material of the nozzle, the high performance of the HAN propellant cannot be fully exerted. On the premise of satisfying light weight, high temperature resistance and oxidation resistance, when the combustion temperature reaches over 1200 ℃, the change of the organization, the mechanical property, the oxidation resistance, the thermophysical property and the like of the SiBCN amorphous ceramic material can play an important role in the long-time continuous and stable work of the engine.
Meanwhile, under the normal-temperature starting condition of the HAN-based thruster, the structure of the catalytic bed has different requirements on the initial stage and the middle and later stages of catalytic decomposition of the propellant, and the structural design of the catalytic bed directly influences the starting and stable working processes of the engine. The traditional catalytic bed structure is no longer suitable, and it is necessary to design a modular catalytic bed structure with long life, with the concept of high reliability, low cost and light weight, so as to have high matching among the engine, the propellant and the catalyst.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the ceramic thrust chamber for the single-component hydroxyl nitrate amino thruster is provided, and the design requirements of the liquid rocket engine on high reliability, light weight and low engine are met.
The purpose of the invention is realized by the following technical scheme: a ceramic thrust chamber for a one-component hydroxyl nitrate based thruster, comprising: placing steps, a catalytic front bed, a catalytic middle bed, a catalytic rear bed, a double-arc spray pipe, a front bed baffle, a middle bed baffle and a rear bed baffle; the left end face of the placing step is connected with an external sealing gasket, and the right end face of the placing step is movably connected with an external injector; the right end surface of the catalytic forebed is connected with the lower end surface of the forebed baffle; the right end face of the catalytic middle bed is connected with the lower end face of the middle bed baffle; the right end surface of the catalytic rear bed is connected with the lower end surface of the rear bed baffle.
In the above ceramic thrust chamber for a mono-component hydroxyl-amino nitrate thruster, the diameter of the pre-catalytic bed is D, the diameter of the middle catalytic bed is D, and the diameter of the post-catalytic bed is D, wherein the relationship between D, D and D satisfies the following formula: d21-D31≥3mm，D31-D41≥3mm。
In the ceramic thrust chamber for the mono-component hydroxyl-amino nitrate thruster, the diameter of the outer end of the catalytic fore-bed is D, and the wall thickness of the catalytic fore-bed is D22The wall thickness of the catalytic middle bed is D32The wall thickness of the catalytic bed is D42Wherein D is22、D32And D42Satisfies the formula: d21+D22＝D31+D32＝D41+D42＝D。
In the ceramic thrust chamber for the single-component hydroxyl-amino nitrate thruster, the length of the catalytic fore-bed is L23The length of the catalytic middle bed is L33The wall thickness of the catalytic bed is L43Wherein L is23、L33And L43Satisfies the formula: l is23-L33≥30mm，L33-L43≥10mm。
In the ceramic thrust chamber for the single-component hydroxyl-amino nitrate thruster, the diameter of the placing step is D11，D11、D21And D satisfies the formula: d11-D≥6mm，D-D21≥4mm。
In the ceramic thrust chamber for the single-component hydroxyl nitrate amino thruster, the throat diameter of the double-arc spray pipe is D52The diameter of the outlet of the double-arc spray pipe is D53Wherein D is52And D53Satisfies the formula: d53/D52＝10。
In the ceramic thrust chamber for the mono-component hydroxyl nitrate amino thruster, the diameter of the front bed baffle is D51A plurality of holes with the diameter D are arranged at the center of the tube52The distance between two adjacent first cylindrical holes is 1mm, and the thickness of the front bed baffle is 1 mm.
In the ceramic thrust chamber for the mono-component hydroxyl nitrate amino thruster, the diameter of the middle bed baffle is D61At the center of which is provided with a diameter D52The distance between two adjacent second cylindrical holes is 1mm, and the thickness of the middle bed baffle plate is 1.5 mm.
In the ceramic thrust chamber for the single-component hydroxyl-amino nitrate thruster, the diameter of the back bed baffle is D71At the center of which is provided with a diameter D52The distance between two adjacent third cylindrical holes is 1mm, and the thickness of the back bed baffle plate is 2 mm.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention can be used for the design of ceramic thrust chambers for HAN-based engines with different magnitudes by establishing the structures of the catalytic fore-bed, the catalytic middle-bed and the catalytic after-bed, effectively solves the problem of selection of oxidizing products and high-temperature environment of the HAN-based engine in catalytic decomposition and combustion on engine body materials, and realizes the satisfaction of harsh requirements of repeated ignition at low temperature, oxidation resistance at high temperature and the like of the HAN-based engine thrust chamber;
(2) the invention effectively solves the disadvantages of large density and higher cost of the traditional metal materials such as platinum-rhodium alloy, rhenium-iridium alloy and the like used for the HAN-based engine thrust chamber by establishing the structure of the ceramic thrust chamber, realizes the catalytic decomposition and stable combustion of the HAN-based propellant in the ceramic thrust chamber by adopting the ceramic thrust chamber made of the SiBCN ceramic material with structural stability, high-temperature creep resistance and oxidation resistance, and has relatively low price and low density and can realize long-term stable work. In a single-component thruster product, the single-component thruster has good market popularization;
(3) the invention realizes the structure of the SiBCN ceramic thrust chamber by integrating the catalytic fore-bed, the catalytic middle-bed, the catalytic rear-bed and the double-arc spray pipe through an integrated molding technology, breaks through the procedures that electron beam welding, scanning CT and the like are needed by a sprayer and a thrust chamber, a catalytic bed and the spray pipe in the traditional single-component thruster development process, simultaneously reduces the expense of collaborative design among key components such as the catalytic bed, the spray pipe and the sprayer in the HAN-based engine thrust chamber development process, particularly for the thrust chamber of a high-thrust engine, and can meet the requirements of low cost and light weight of the whole machine. The method can be widely applied to power systems of weapon equipment such as a satellite-borne engine, a carrier rocket, a strategic tactical missile warhead and the like for an HAN base single-component engine.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
FIG. 1 is a cross-sectional view of a ceramic thrust chamber for a one-component hydroxylamino nitrate based thruster provided by an embodiment of the present invention;
FIG. 2 is a schematic cross-sectional view of a front bed baffle provided in an embodiment of the present invention;
FIG. 3 is a schematic cross-sectional view of a mid-bed baffle according to an embodiment of the present invention;
fig. 4 is a schematic cross-sectional view of a back bed baffle provided in the practice of the invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
Figure 1 is a cross-sectional view of a ceramic thrust chamber for a one-component hydroxyl nitrate based thruster provided by an embodiment of the present invention. As shown in fig. 1, the ceramic thrust chamber for a one-component hydroxylamino nitrate based thruster comprises: the device comprises a placing step 1, a catalytic fore-bed 2, a catalytic middle-bed 3, a catalytic after-bed 4, a double-arc spray pipe 5, a fore-bed baffle 6, a middle-bed baffle 7 and a back-bed baffle 8. Wherein the content of the first and second substances,
the left end face 11 of the placing step 1 is connected with an external sealing gasket, and the right end face 12 is movably connected with an external injector; the right end surface of the catalytic front bed 2 is connected with the lower end surface 61 of the front bed baffle 6; the right end face of the catalytic middle bed 3 is connected with the lower end face 71 of the middle bed baffle 7; the right end face of the catalytic rear bed 4 is connected with the lower end face 81 of the rear bed baffle plate 8.
Specifically, one end of the catalytic forebed is connected with an upstream injector through electron beam welding, the other end of the catalytic forebed is connected with one end of a catalytic middle bed, one end of the catalytic middle bed is connected with one end of a catalytic rear bed, the other end of the catalytic rear bed is connected with a double-arc spray pipe, one end of the placing step is connected with the graphite sealing gasket, the other end of the placing step is connected with the metal bracket, the graphite sealing gasket and the metal bracket are combined to achieve the sealing effect of the engine, and the right end face of the catalytic forebed is connected with the lower; the right end face of the catalytic middle bed is connected with the lower end face of the baffle plate of the middle bed; the right end face of the catalytic rear bed is connected with the lower end face of the rear bed baffle.
The materials of the placing step 1, the catalytic fore-bed 2, the catalytic middle-bed 3, the catalytic rear-bed 4, the fore-bed baffle 5, the middle-bed baffle 6, the rear-bed baffle 7 and the double-arc spray pipe 8 are SiBCN ceramic materials. The advantages are that: the hydroxyl-amine nitrate based thruster has the characteristics of high combustion temperature and strong oxidizing property of a large part of products in the self-catalytic decomposition and combustion process, which brings great challenges to the design and material selection of the thrust chamber. At present, a single-component hydrazine engine generally adopts a nickel-based high-temperature alloy material with limited temperature resistance, and the performance of the hydroxylamine nitrate thruster is severely restricted. The low-cost and light-weight SiBCN ceramic material with high temperature resistance and oxidation resistance has excellent properties of structure stability, high-temperature creep resistance, oxidation resistance and the like, is relatively low in price and low in density, and can completely meet the design requirements of the hydroxylamine nitrate-based thruster.
As shown in FIG. 1, the diameter of the catalytic front bed 2 is D21The diameter of the catalytic middle bed 3 is D31The diameter of the catalytic after-bed 4 is D41Wherein D is21、D31And D41Satisfies the formula: d21-D31≥3mm，D31-D41Not less than 3 mm. The advantages are that: under the condition of normal-temperature starting, the structure of the catalytic bed has different requirements on the initial stage and the middle and later stages of catalytic decomposition of the propellant, and the structural design and the size of the catalytic bed directly influence the starting and stable working process of an engine. The design can meet the requirement that the hydroxylamine nitrate based propellant realizes good catalytic decomposition efficiency and combustion stability.
As shown in FIG. 1, the outer end of the catalytic front bed 2 has a diameter D, and the wall thickness of the catalytic front bed 2 is D22The wall thickness of the catalytic middle bed 3 is D32The wall thickness of the catalytic after-bed 4 is D42Wherein D is22、D32And D42Satisfies the formula: d21+D22＝D31+D32＝D41+D42D. . With the gradual starting of the combustion reaction, the catalytic middle bed and the catalytic rear bed bear the impact of higher combustion temperature and heat back-leaching effect, so the design can keep the combustion pressure fluctuation small and can meet the requirement of enough strength.
As shown in FIG. 1, the length of the catalytic front bed 2 is L23The length of the catalytic middle bed 3 is L33The wall thickness of the catalytic after-bed 4 is L43Wherein L is23、L33And L43Satisfies the formula: l is23-L33≥30mm，L33-L43Not less than 10 mm. At normal temperature start-up, before catalysisThe bed needs to meet the requirement that the hydroxylamine nitrate propellant is rapidly decomposed in a front bed; while the middle catalytic bed needs to relieve the scouring force to maintain the flame at the front end of the catalytic bed, so that the influence on the service life of the catalyst is reduced, and the catalytic bed plays an important role in the stability of the flow resistance characteristic and the combustion reaction. Therefore, the design can meet the requirements of different areas of a catalytic bed on catalytic decomposition and combustion reaction, and is favorable for meeting the design requirement of long-life modularization of the thrust chamber.
As shown in FIG. 1, the diameter of the placing step 1 is D11，D11、D21And D satisfies the formula: d11-D≥6mm，D-D21Not less than 4 mm. Under the catalytic decomposition and combustion reaction environment of high-temperature strong oxidation, effective heat exchange effect can be realized on the one hand by the wall surface larger than 2mm, and on the other hand, the catalytic fore-bed has enough strength. Meanwhile, the design of the placing step is beneficial to realizing the reliable connection between the thrust chamber and the upstream injector.
As shown in FIG. 1, the throat diameter of the double-arc nozzle 5 is D52The diameter of the outlet of the double-arc spray pipe 5 is D53Wherein D is52And D53Satisfies the formula: d53/D5210. When the area is the same, adopt the biarc spray tube to compare in the length of toper spray tube and special type spray tube shorter, can realize good gas expansion, suitable expansion ratio simultaneously can satisfy spray tube efficiency increase, and the specific impulse loss reduces.
As shown in FIG. 2, the front bed baffle 6 has a diameter D51A plurality of holes with the diameter D are arranged at the center of the tube52The distance between two adjacent first cylindrical holes is 1mm, and the thickness of the front bed baffle 6 is 1 mm. In the embodiment, the front bed baffle is arranged between the catalytic front bed and the catalytic middle bed, on one hand, the filling requirement of the catalyst is met, on the other hand, enough flow channels and enough strength can be realized, the flow control is realized, the good combustion stability is maintained,
as shown in figure 3, the diameter of the middle bed baffle 7 is D61At the center of which is provided with a diameter D52The distance between two adjacent second cylindrical holes is 1mm,the thickness of the middle bed baffle 7 is 1.5 mm. Bed and catalysis after the bed in the installation catalysis of bed baffle in this embodiment, can reduce propellant catalytic decomposition and combustion reaction in-process to the influence of catalyst life-span, along with the gradual start-up of combustion reaction, need compare in preceding bed baffle simultaneously, and the thickness of bed baffle needs to increase to realize that water conservancy erodees and flame propagation in-process bed baffle can provide sufficient intensity and support.
As shown in FIG. 4, the diameter of the back bed baffle 8 is D71At the center of which is provided with a diameter D52The distance between two adjacent third cylindrical holes is 1mm, and the thickness of the back bed baffle 8 is 2 mm. The embodiment can realize the stability of flowing and burning between the bed and the biarc spray tube after the back bed baffle installation catalysis, simultaneously along with the combustion reaction with the hot joint influence who soaks the effect back, need compare in well bed baffle, need increase the thickness of back bed baffle to satisfy back bed baffle and can satisfy to have sufficient intensity and resistant scouring ability under the high temperature condition.
The structure of the catalytic fore-bed, the catalytic middle-bed and the catalytic after-bed is established, the ceramic thrust chamber can be used for designing ceramic thrust chambers for HAN-based engines with different magnitudes, the problem of selection of oxidizing products and high-temperature environment of the HAN-based engine in catalytic decomposition and combustion is effectively solved, and the harsh requirements of repeated ignition at low temperature, oxidation resistance at high temperature and the like of the HAN-based engine thrust chamber are met.
The ceramic thrust chamber manufactured by the SiBCN ceramic material with the structure stability, the high-temperature creep resistance and the oxidation resistance realizes the catalytic decomposition and the stable combustion of the HAN-based propellant in the ceramic thrust chamber, and has relatively low price and low density, and can realize the long-term stable work. In a single-component thruster product, the single-component thruster has good market popularization;
in the embodiment, the SiBCN ceramic thrust chamber structure is realized by integrating the front catalytic bed, the middle catalytic bed, the rear catalytic bed and the double-arc spray pipe through an integrated forming technology, the processes that an injector and a thrust chamber, a catalytic bed and the spray pipe need electron beam welding, scanning CT and the like in the traditional single-component thruster development process are broken through, the HAN-based engine thrust chamber is reduced, especially the cost of collaborative design among key components such as the catalytic bed, the spray pipe and the injector in the high-thrust engine thrust chamber development process is reduced, and the requirement of low cost and light weight of the whole machine can be met. The method can be widely applied to power systems of weapon equipment such as a satellite-borne engine, a carrier rocket, a strategic tactical missile warhead and the like for an HAN base single-component engine.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. A ceramic thrust chamber for a monopropellant hydroxyl-amino nitrate thruster, comprising: placing a step (1), a catalytic front bed (2), a catalytic middle bed (3), a catalytic rear bed (4), a double-arc spray pipe (5), a front bed baffle (6), a middle bed baffle (7) and a rear bed baffle (8); wherein the content of the first and second substances,
the left end face (11) of the placing step (1) is connected with an external sealing gasket, and the right end face (12) of the placing step (1) is movably connected with an external injector;
the right end face of the catalytic front bed (2) is connected with the lower end face (61) of the front bed baffle plate (6);
the right end face of the catalytic middle bed (3) is connected with the lower end face (71) of the middle bed baffle plate (7);
the right end face of the catalytic rear bed (4) is connected with the lower end face (81) of the rear bed baffle (8).
2. The ceramic thrust chamber for a monopropellant hydroxyl-nitrate-based thruster of claim 1, wherein: the material of the placing step (1), the catalytic fore-bed (2), the catalytic middle-bed (3), the catalytic rear-bed (4), the double-arc spray pipe (5), the fore-bed baffle (6), the middle-bed baffle (7) and the rear-bed baffle (8) is SiBCN ceramic material.
3. The ceramic thrust chamber for a monopropellant hydroxyl-nitrate-based thruster of claim 1, wherein: the diameter of the catalytic front bed (2) is D21The diameter of the catalytic middle bed (3) is D31The diameter of the catalytic after-bed (4) is D41Wherein D is21、D31And D41Satisfies the formula: d21-D31≥3mm，D31-D41≥3mm。
4. The ceramic thrust chamber for a monopropellant hydroxyl-nitrate-based thruster of claim 3, wherein: the diameter of the outer end of the catalytic fore-bed (2) is D, and the wall thickness of the catalytic fore-bed (2) is D22The wall thickness of the catalytic middle bed (3) is D32The wall thickness of the catalytic after-bed (4) is D42Wherein D is22、D32And D42Satisfies the formula: d21+D22＝D31+D32＝D41+D42＝D。
5. The ceramic thrust chamber for a monopropellant hydroxyl-nitrate-based thruster of claim 4, wherein: the length of the catalytic fore-bed (2) is L23The length of the catalytic middle bed (3) is L33The wall thickness of the catalytic after-bed (4) is L43Wherein L is23、L33And L43Satisfies the formula: l is23-L33≥30mm，L33-L43≥10mm。
6. The ceramic thrust chamber for a monopropellant hydroxyl-nitrate-based thruster of claim 4,the method is characterized in that: the diameter of the placing step (1) is D11，D11、D21And D satisfies the formula: d11-D≥6mm，D-D21≥4mm。
7. The ceramic thrust chamber for a monopropellant hydroxyl-nitrate-based thruster of claim 5, wherein: the throat diameter of the double-arc spray pipe (5) is D52The diameter of the outlet of the double-arc spray pipe (5) is D53Wherein D is52And D53Satisfies the formula: d53/D52＝10。
8. The ceramic thrust chamber for a monopropellant hydroxyl-nitrate-based thruster of claim 1, wherein: the diameter of the front bed baffle (6) is D51A plurality of holes with the diameter D are arranged at the center of the tube52The distance between two adjacent first cylindrical holes is 1mm, and the thickness of the front bed baffle (6) is 1 mm.
9. The ceramic thrust chamber for a monopropellant hydroxyl-nitrate-based thruster of claim 1, wherein: the diameter of the middle bed baffle (7) is D61At the center of which is provided with a diameter D52The distance between two adjacent second cylindrical holes is 1mm, and the thickness of the middle bed baffle (7) is 1.5 mm.
10. The ceramic thrust chamber for a monopropellant hydroxyl-nitrate-based thruster of claim 1, wherein: the diameter of the back bed baffle (8) is D71At the center of which is provided with a diameter D52The distance between two adjacent third cylindrical holes is 1mm, and the thickness of the back bed baffle (8) is 2 mm.
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| CN111550328A (en) * | 2020-05-09 | 2020-08-18 | 北京控制工程研究所 | Ignition method for realizing rapid normal-temperature start of hydroxylamine nitrate engine |
| CN113530715A (en) * | 2021-09-16 | 2021-10-22 | 西安空天引擎科技有限公司 | Pumping pressure type engine starting ignition method and system based on hydrogen peroxide |
| CN115073200A (en) * | 2022-05-19 | 2022-09-20 | 北京控制工程研究所 | Butt-joint sealing structure and method for ceramic reaction chamber and high-temperature alloy injector |
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| CN110645117B (en) | 2021-02-09 |
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