CN112431675B - A combined scramjet cooling cycle system - Google Patents
A combined scramjet cooling cycle system Download PDFInfo
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- 238000001816 cooling Methods 0.000 title claims abstract description 108
- 239000000446 fuel Substances 0.000 claims abstract description 32
- 229910001338 liquidmetal Inorganic materials 0.000 claims abstract description 20
- 238000002485 combustion reaction Methods 0.000 claims abstract description 18
- 239000002828 fuel tank Substances 0.000 claims abstract description 12
- 239000003350 kerosene Substances 0.000 claims abstract description 11
- 238000002955 isolation Methods 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 4
- 229910001152 Bi alloy Inorganic materials 0.000 claims description 3
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- 229910000799 K alloy Inorganic materials 0.000 claims description 3
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 3
- 229910000978 Pb alloy Inorganic materials 0.000 claims description 3
- 229910052792 caesium Inorganic materials 0.000 claims description 3
- TVFDJXOCXUVLDH-UHFFFAOYSA-N caesium atom Chemical compound [Cs] TVFDJXOCXUVLDH-UHFFFAOYSA-N 0.000 claims description 3
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- 229910052744 lithium Inorganic materials 0.000 claims description 3
- 238000000034 method Methods 0.000 claims description 3
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- BITYAPCSNKJESK-UHFFFAOYSA-N potassiosodium Chemical compound [Na].[K] BITYAPCSNKJESK-UHFFFAOYSA-N 0.000 claims description 3
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- 229910052708 sodium Inorganic materials 0.000 claims description 3
- 239000011734 sodium Substances 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims 2
- 229910045601 alloy Inorganic materials 0.000 claims 1
- 239000000956 alloy Substances 0.000 claims 1
- 238000002347 injection Methods 0.000 claims 1
- 239000007924 injection Substances 0.000 claims 1
- 238000012546 transfer Methods 0.000 abstract description 7
- 230000008929 regeneration Effects 0.000 abstract description 6
- 238000011069 regeneration method Methods 0.000 abstract description 6
- 239000002918 waste heat Substances 0.000 abstract description 6
- 238000004939 coking Methods 0.000 abstract description 5
- 238000005336 cracking Methods 0.000 abstract description 5
- 230000006866 deterioration Effects 0.000 abstract description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 10
- 239000002826 coolant Substances 0.000 description 8
- 230000004907 flux Effects 0.000 description 6
- 239000007788 liquid Substances 0.000 description 5
- 229910052757 nitrogen Inorganic materials 0.000 description 5
- 239000000295 fuel oil Substances 0.000 description 4
- 230000001172 regenerating effect Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 229910000846 In alloy Inorganic materials 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000018109 developmental process Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
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- 238000006467 substitution reaction Methods 0.000 description 1
- 239000002912 waste gas Substances 0.000 description 1
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Classifications
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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
- F02C7/22—Fuel supply systems
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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
- F02C7/16—Cooling of plants characterised by cooling medium
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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
- F02C7/22—Fuel supply systems
- F02C7/224—Heating fuel before feeding to the burner
-
- 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
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- 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
- F23R3/005—Combined with pressure or heat exchangers
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- 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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
Description
技术领域technical field
本发明属于吸气式超燃冲压发动机热防护技术领域，具体涉及一种组合式的超燃冲压发动机冷却循环系统。The invention belongs to the technical field of thermal protection of an air-breathing scramjet, in particular to a combined cooling cycle system of a scramjet.
背景技术Background technique
先进高超声速飞行器的发展是国家综合实力的重要象征，其对军事战略、国民经济和社会生活产生重大意义，而目前马赫数Ma>5的飞行器是人类对更高飞行速度的追求产物。但随着对飞行马赫数和巡航时间需求的增加，由于高焓来流和燃烧释热，燃烧室热环境极其严酷，先进飞行器发动机壁面冷却问题越来越突出。例如超燃冲压发动机飞行高度处于25km，马赫数达到6.5时，飞行器会承受超过1800K的入口来流空气温度、高达2800K的壁面燃气温度及10MW/m2的热流密度。研究发现即使壁面温度处于1000K时，其仍承受兆瓦级别的热流密度，若发动机壁面急剧升高，必导致壁面材料热蚀，造成热防护失败。The development of advanced hypersonic aircraft is an important symbol of a country's comprehensive strength, which is of great significance to military strategy, national economy and social life, and the current aircraft with Mach number Ma>5 is the product of human pursuit of higher flight speed. However, with the increasing demand for flight Mach number and cruising time, due to high enthalpy inflow and combustion heat release, the thermal environment of the combustion chamber is extremely harsh, and the problem of wall cooling of advanced aircraft engines is becoming more and more prominent. For example, when the flight altitude of the scramjet is 25km and the Mach number reaches 6.5, the aircraft will withstand the inlet air temperature exceeding 1800K, the wall gas temperature as high as 2800K and the heat flux density of 10MW/m 2 . The study found that even when the wall surface temperature is 1000K, it still bears the heat flux density of megawatt level. If the engine wall surface increases sharply, it will inevitably lead to thermal corrosion of the wall surface material, resulting in the failure of thermal protection.
在众多超燃冲压发动机热防护技术中，以航空煤油为冷却剂、采用废热再利用技术的再生冷却方式备受广泛关注。然而受该技术本身限制，使得再生冷却面临诸多挑战，如燃料高温裂解结焦、热沉不足、非对称受热壁面热载荷不均匀、系统动态特性复杂等，这和单一使用一种燃料冷源有直接关系。而如何摆脱传统煤油再生冷却思维束缚，找到另外一种先进冷却工质作为辅助冷源，两者合理布置，以期联合循环提升热防护能力，显得尤为重要。Among the many thermal protection technologies for scramjets, the regenerative cooling method using aviation kerosene as the coolant and using the waste heat reuse technology has received extensive attention. However, due to the limitations of the technology itself, regenerative cooling faces many challenges, such as high-temperature pyrolysis of fuel, insufficient heat sink, uneven thermal load on asymmetric heated walls, complex system dynamic characteristics, etc. relation. How to get rid of the traditional kerosene regeneration and cooling thinking, find another advanced cooling medium as an auxiliary cold source, and arrange the two reasonably, in order to improve the thermal protection capability of the combined cycle, it is particularly important.
专利“超燃冲压发动机水冷装置”(CN 205955856 U)提出一种水冷方案，采用水箱、雾化喷嘴及尾喷管等装置，可以有效吸收超燃冲压发动机多余热量，而且全局设备装置结构简单，且提高了系统安全性。但水的存储相对困难，且沸点很小，而且流体易发生两相变化，不利于再生冷却通道内换热能力的进一步挖掘。专利“超燃冲压发动机液氮冷却系统”(CN 201510433952.7)公开了一种采用液氮来冷却超燃冲压发动机壁面温度的方案，配套的相关装置有液氮供应、高压气源、高压集气等设备，旨在对壁面温度进行有效冷却，而且系统更加安全和可靠。但冷却系统依然存在一些问题，一方面，即使液氮具有较大的热沉能力且不会发生裂解结焦问题，可以作为循环系统中的冷却剂，但该工质需处于高压状态且需废气收集，会额外增加复杂的配套装置，会带来飞行器的质量惩罚。另一方面，液氮冷却剂属于传统冷却工质，而随着高超声速吸气式飞行器的快速发展，需要进一步挖掘先进的高换热性能的新冷却剂工质，可以使得冷却系统结构更加简单，且冷却性能有较大提高。The patent "Water-cooling device for scramjet engine" (CN 205955856 U) proposes a water-cooling scheme, which adopts devices such as water tank, atomizing nozzle and tail nozzle, which can effectively absorb excess heat of scramjet engine, and the overall structure of the equipment is simple, And improve system security. However, the storage of water is relatively difficult, and the boiling point is very small, and the fluid is prone to two-phase changes, which is not conducive to further excavation of the heat exchange capacity in the regenerative cooling channel. The patent "Scramjet Liquid Nitrogen Cooling System" (CN 201510433952.7) discloses a scheme of using liquid nitrogen to cool the wall temperature of a scramjet engine. The supporting related devices include liquid nitrogen supply, high-pressure gas source, high-pressure gas collection, etc. equipment, designed to effectively cool the wall temperature, and the system is safer and more reliable. However, there are still some problems in the cooling system. On the one hand, even if the liquid nitrogen has a large heat sink capacity and will not have the problem of cracking and coking, it can be used as a coolant in the circulating system, but the working medium needs to be in a high pressure state and the waste gas needs to be collected. , additional complex supporting devices will be added, which will bring the quality penalty of the aircraft. On the other hand, liquid nitrogen coolant is a traditional cooling medium, and with the rapid development of hypersonic air-breathing aircraft, it is necessary to further explore new advanced coolant with high heat transfer performance, which can make the structure of the cooling system simpler , and the cooling performance has been greatly improved.
发明内容SUMMARY OF THE INVENTION
要解决的技术问题：Technical problem to be solved:
为了避免现有技术的不足之处，本发明提出一种组合式的超燃冲压发动机冷却循环系统，通过开式和闭式循环相结合，闭式循环中采用液态金属进行换热，解决了超燃冲压发动机再生冷却困难、冷却燃料过度裂解结焦、热沉及冷源严重不足问题，通过一种不同于传统煤油的先进辅助冷却工质，用以构建组合循环系统，以提高系统热防护能力。In order to avoid the deficiencies of the prior art, the present invention proposes a combined scramjet cooling cycle system. By combining open and closed cycles, liquid metal is used for heat exchange in the closed cycle, which solves the problem of overheating. The ramjet is difficult to regenerate and cool, the cooling fuel is excessively cracked and coked, and the heat sink and the cold source are seriously insufficient. An advanced auxiliary cooling medium different from traditional kerosene is used to build a combined circulation system to improve the thermal protection capability of the system.
本发明的技术方案是：一种组合式的超燃冲压发动机冷却循环系统，包括冷却通道，所述冷却通道位于发动机外壳体的内、外壁面之间的环形空腔内；其特征在于：还包括燃料箱、燃料泵、换热器、燃油喷注器和电磁泵；The technical scheme of the present invention is: a combined scramjet cooling cycle system, comprising a cooling channel, the cooling channel is located in the annular cavity between the inner and outer walls of the outer casing of the engine; it is characterized in that: Including fuel tank, fuel pump, heat exchanger, fuel injector and solenoid pump;
所述冷却通道内沿径向设置有环形隔板，将冷却通道分割为相互独立的第一冷却通道和第二冷却通道；与超燃冲压发动机进气道和隔离段相对位置的环形空腔为第一冷却通道，与超燃冲压发动机燃烧室及尾喷管相对位置的环形空腔为第二冷却通道；An annular partition plate is arranged in the cooling channel along the radial direction, and the cooling channel is divided into a first cooling channel and a second cooling channel that are independent of each other; the annular cavity opposite to the scramjet intake channel and the isolation section is The first cooling channel, the annular cavity relative to the scramjet combustion chamber and the tail nozzle is the second cooling channel;
所述燃料箱、燃料泵、换热器、第一冷却通道和燃油喷注器依次通过管道连接，形成开式冷却循环系统，所述开式冷却循环系统的工质为煤油；所述电磁泵、第二冷却通道和换热器依次通过管道连接，形成闭式冷却循环系统，所述闭式冷却循环系统内的循环的工质为液态金属。The fuel tank, the fuel pump, the heat exchanger, the first cooling channel and the fuel injector are sequentially connected by pipelines to form an open cooling circulation system, and the working medium of the open cooling circulation system is kerosene; the electromagnetic pump , the second cooling channel and the heat exchanger are sequentially connected by pipes to form a closed cooling cycle system, and the circulating working medium in the closed cooling cycle system is liquid metal.
本发明的进一步技术方案是：所述液态金属为铅、钠、锂、铯、铷，钠钾合金、铅铋合金、锂铅合金和嫁铟合金中的一种或多种组合。A further technical scheme of the present invention is: the liquid metal is one or more combinations of lead, sodium, lithium, cesium, rubidium, sodium-potassium alloy, lead-bismuth alloy, lithium-lead alloy and indium alloy.
本发明的进一步技术方案是：所述的液态金属的流量可通过电磁泵自动控制，使冷却后的壁面温度远远低于燃烧室壁面材料的温度极限。The further technical scheme of the present invention is that the flow rate of the liquid metal can be automatically controlled by an electromagnetic pump, so that the cooled wall temperature is far lower than the temperature limit of the combustion chamber wall material.
本发明的进一步技术方案是：所述环形隔板位于超燃冲压发动机的隔离段与燃烧室之间的对应位置。A further technical solution of the present invention is that: the annular baffle is located at a corresponding position between the isolation section of the scramjet and the combustion chamber.
本发明的进一步技术方案是：所述第一冷却通道的内壁面开有通孔，作为第一冷却通道的出口，与连接燃油喷注器的管道密封连接；所述第二冷却通道的外壁面开有通孔，作为第二冷却通道的入口，与连接电磁泵的管道密封连接。A further technical solution of the present invention is that: the inner wall surface of the first cooling channel is provided with a through hole, which is used as the outlet of the first cooling channel to be sealed with the pipeline connecting the fuel injector; the outer wall surface of the second cooling channel A through hole is opened, which serves as the inlet of the second cooling channel, and is connected with the pipeline connected to the electromagnetic pump in a sealed manner.
有益效果beneficial effect
本发明的有益效果在于：1)液态金属的普朗特数非常小，温度边界层厚度远大于速度边界层的厚度，因而液态金属对流传热主要通过层内分子热传导进行，具有较强的换热性能，高热流密度壁面区域的热负荷易被带走，极大的削弱了壁面温度，且可以有效避免类似超临界流体发生的传热恶化极端工况，更不存在裂解结焦问题；2)液态金属辅助冷却循环系统有效缓解了煤油吸热温升以致发生裂解结焦的情况，且分别将液态金属闭式冷却循环和煤油再生开式冷却循环布置于高热流密度壁面区域和低热流密度壁面区域，可有效避免煤油温升过高发生堵塞冷却通道的情况；3)本发明既利用了发动机燃烧室壁面的废热，保留了主动再生冷却系统的优势，又解决了传统冷却工质存在的传热恶化、裂解结焦等问题，构建了高效的能量管理循环系统。依据相同工况下超燃冲压发动机工作过程和壁面传热分析，本发明方案下的极端热流密度远远低于传统的煤油冷却再生方案，更远远小于发动机壁面材料的极限温度1200K。The beneficial effects of the present invention are: 1) The Prandtl number of the liquid metal is very small, and the thickness of the temperature boundary layer is much larger than the thickness of the velocity boundary layer, so the convective heat transfer of the liquid metal is mainly carried out by the heat conduction of the molecules in the layer, which has a strong exchange rate. Thermal performance, the heat load in the wall area with high heat flux density is easily taken away, which greatly weakens the wall temperature, and can effectively avoid the extreme working conditions of heat transfer deterioration similar to supercritical fluids, and there is no problem of cracking and coking; 2) The liquid metal auxiliary cooling cycle system effectively alleviates the heat-absorbing temperature rise of kerosene and causes cracking and coking, and the liquid metal closed cooling cycle and kerosene regeneration open cooling cycle are respectively arranged in the high heat flux density wall area and the low heat flux density wall area. , which can effectively avoid the situation that the kerosene temperature rises too high to block the cooling channel; 3) The invention not only utilizes the waste heat of the engine combustion chamber wall, retains the advantages of the active regenerative cooling system, but also solves the heat transfer existing in the traditional cooling medium. Deterioration, cracking and coking and other problems, an efficient energy management cycle system has been constructed. According to the working process and wall heat transfer analysis of the scramjet engine under the same working conditions, the extreme heat flux density under the solution of the present invention is far lower than that of the traditional kerosene cooling and regeneration solution, and is far lower than the limit temperature of 1200K of the engine wall material.
附图说明Description of drawings
图1是本发明实施例1中的系统结构示意图；1 is a schematic diagram of a system structure in
图2是本发明的组合冷却循环工作原理示意图；2 is a schematic diagram of the working principle of the combined cooling cycle of the present invention;
附图标记说明：1.燃料箱，2.燃料泵，3.换热器，4.第一冷却通道，5.燃油喷注器，6.电磁泵，7.第二冷却通道，8.进气道，9.隔离段，10.燃烧室，11.尾喷管。DESCRIPTION OF REFERENCE NUMERALS: 1. Fuel tank, 2. Fuel pump, 3. Heat exchanger, 4. First cooling passage, 5. Fuel injector, 6. Electromagnetic pump, 7. Second cooling passage, 8. Inlet Airway, 9. Isolation section, 10. Combustion chamber, 11. Tail nozzle.
具体实施方式Detailed ways
下面通过参考附图描述的实施例是示例性的，旨在用于解释本发明，而不能理解为对本发明的限制。The embodiments described below with reference to the accompanying drawings are exemplary, and are intended to explain the present invention and should not be construed as limiting the present invention.
参照图1所述，本发明一种组合式的超燃冲压发动机冷却循环系统，包括开式冷却循环系统和闭式冷却循环系统；所述开式冷却循环系统中工质为煤油；所述闭式冷却循环系统中工质为液态金属，所述液态金属为铅、钠、锂、铯、铷，钠钾合金、铅铋合金、锂铅合金和嫁铟合金中的一种或多种组合。1, a combined scramjet cooling cycle system of the present invention includes an open cooling cycle system and a closed cooling cycle system; the working medium in the open cooling cycle system is kerosene; the closed cooling cycle system The working medium in the cooling circulation system is liquid metal, and the liquid metal is one or more combinations of lead, sodium, lithium, cesium, rubidium, sodium-potassium alloy, lead-bismuth alloy, lithium-lead alloy and indium alloy.
所述开式冷却循环系统实属燃料流动冷却侧，包括燃料箱1、燃料泵2、换热器3、第一冷却通道4，燃油喷注器5，所有部件之间都是通过管道进行连接。所述燃料箱1连接于燃料泵2入口，所述换热器3连接于燃料泵2出口和第一冷却通道4之间，所述第一冷却通道4位于进气道和隔离段外侧壁面处，所述燃油喷注器位于燃烧室10中且连接于第一冷却通道4出口。所述闭式冷却循环系统实属液态金属流动冷却侧，重要部件之间通过管道进行连接。所述第二冷却通道7位于燃烧室和尾喷管外侧壁面处，所述电磁泵连接于换热器出口和第二冷却通道7之间、所述换热器3连接于第二冷却通道7出口和电磁泵6之间。The open cooling cycle system is actually the cooling side of the fuel flow, including the
结合图2说明实施方案的具体原理如下：1)开式燃油冷却循环侧。燃油从燃料箱1开始经过开式冷却循环后被注入进燃烧室10中燃烧，系统中冷源为燃料箱1中携带的燃油，热源为第一冷却通道4中的热负荷；其中，燃料泵2位于燃料箱1后，为换热器3和第一冷却通道4提供可调控的流量；燃料首先被注入到换热器3中，和高温液态金属发生热交换，燃料温度升高完成初步的再生废热利用，并进入第一冷却通道4中吸收废热完成第二步的再生利用，再经过燃油喷注器5，雾化状态的燃油被注入到燃烧室10中燃烧，完成燃料侧开式冷却循环；2)闭式冷却循环侧。该循环中冷源为低温液态金属，热源为冷却通道7中的热负荷，其中液态金属为载热循环工质；低温液态金属经过电磁泵6后被注入到壁面高热负荷的第二冷却通道7中吸收燃烧室10中的废热，温升的液态金属进入到换热器3中和燃油进行热交换，将热量传递给燃油而达到温降的目的，并由电磁泵6再次注入进第二冷却通道7内完成闭式冷却循环。The specific principles of the embodiment described with reference to FIG. 2 are as follows: 1) Open fuel cooling cycle side. The fuel oil is injected into the
尽管上面已经示出和描述了本发明的实施例，可以理解的是，上述实施例是示例性的，不能理解为对本发明的限制，本领域的普通技术人员在不脱离本发明的原理和宗旨的情况下在本发明的范围内可以对上述实施例进行变化、修改、替换和变型。Although the embodiments of the present invention have been shown and described above, it should be understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and those of ordinary skill in the art will not depart from the principles and spirit of the present invention Variations, modifications, substitutions, and alterations to the above-described embodiments are possible within the scope of the present invention without departing from the scope of the present invention.
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