CN103615741B - Heat protection method for injection support plate of scramjet engine by utilizing sweat and impingement cooling - Google Patents
Heat protection method for injection support plate of scramjet engine by utilizing sweat and impingement cooling Download PDFInfo
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- CN103615741B CN103615741B CN201310561173.6A CN201310561173A CN103615741B CN 103615741 B CN103615741 B CN 103615741B CN 201310561173 A CN201310561173 A CN 201310561173A CN 103615741 B CN103615741 B CN 103615741B
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Abstract
The invention relates to a heat protection method for an injection support plate of a scramjet engine by utilizing sweat and impingement cooling. The method includes the following steps that (1) a high-temperature-resistant material is used for making the injection support plate of a microporous structure, a supporting rib is arranged in the injection support plate and partitions the same into a front cavity and a rear cavity, impingement pores communicated with the front and rear cavities are formed in the supporting rib, and a fuel pipe of the scramjet engine is communicated with the rear cavity of the injection support plate; (2) by the process that fuel seeps out of pores of the injection support plate of the microporous structure, convection heat transfer is carried out forcedly to remove heat on the surface of the injection support plate, and the fuel seeps out of the surface of the injection support plate to form a film layer so as to block heat transfer of the mainstream to the injection support plate; (3) the fuel is injected from the rear cavity to the inner surface of the front cavity via the impingement pores in the supporting rib so as to perform convection heat transfer with the inner surface of the front cavity, and strength of the injection support plate is enhanced by the aid of the supporting rib in the injection support plate. Heat protection effect on the injection support plate is realized by combining the concept of impingement cooling and utilizing the fuel as a cooling agent according to porous medium characteristics, and the method can be widely applied to heat protection of injection support plates of scramjet engines in various Mach working ranges.
Description
Technical field
The present invention relates to a kind of high-temperature wall surface heat protection method, particularly about a kind of sweating and impinging cooling of utilizing in high-temperature high-speed airflow to the thermal protection method of super burn engine spray support plate.
Background technology
Scramjet engine refers to that fuel carries out the punching engine burnt in supersonic flow.When adopting hydrocarbon fuel, the flight Mach number of scramjet engine is usually below 8, and when using Liquid Hydrogen fuel, its flight Mach number can reach 6 ~ 25.As shown in Figure 1, supersonic speed or hypersonic air-flow decelerate to comparatively low supersonic at inducer and distance piece diffusion and enter into combustion chamber, fuel sprays into from the protrusion combustion chamber wall surface and/or air-flow, mixes, burns with air, and the gas after burning is discharged through the nozzle section of expanding.Because the holdup time of fuel in combustion chamber only has several millisecond, there is the short shortcoming of penetration range in the mode of combustion chamber wall surface spray fuel in traditional, is difficult to the effective blending realized between fuel and high speed main flow, affects fuel ignition and burning.
It is the indoor a kind of common device realizing fuel and the effective blending of high speed main flow of current combustion that plate structure is propped up in spray, fuel sprays from the nozzle opening spray support plate, mix with high speed main flow, to overcome the short shortcoming of the incident penetration range of wall, but hypersonic air-flow will produce serious Aerodynamic Heating in spray support plate surface stagnation simultaneously, very easily there is ablative degradation in spray support plate especially its leading edge portion, it is estimated, aircraft with Mach number 8 when the high-altitude flight of height above sea level 27km, the high-temperature fuel gas stagnation temperature flowing through combustion chamber can reach more than 3000K, close to the maximum one of the forced convertion cooling of the fuel adopted at present, more efficiently active cooling method must be adopted to reduce spray support plate surface temperature.
Summary of the invention
For the problems referred to above, the object of this invention is to provide a kind of sweating and impinging cooling of utilizing in high-temperature high-speed airflow to the thermal protection method of super burn engine spray support plate.
For achieving the above object, the present invention takes following technical scheme: a kind of sweating and impinging cooling of utilizing is to the thermal protection method of super burn engine spray support plate, it comprises following content: the spray support plate 1) producing multi-cellular structure with exotic material, the ribs that one is divided into front cavity and rear cavity is set in spray support plate, ribs is provided with the impact opening being communicated with forward and backward cavity, by the rear cavity connects of the cartridge of super burn engine and spray support plate; 2) utilize fuel to ooze out the process of multi-cellular structure spray support plate hole, force to carry out heat convection, take away the heat on spray support plate surface, and utilize fuel to ooze out at spray support plate surface formation thin layer, intercept main flow to the heat transfer of spray support plate; 3) utilize fuel to be ejected into front cavity inner surface from the impact opening of rear cavity through ribs, carry out heat convection with front cavity inner surface, utilize the ribs in spray support plate to strengthen the intensity of spray support plate simultaneously.
Described spray support plate offers the nozzle opening of some 0.5mm.
The outer shape of described spray support plate is carry out the rhombus that flow path direction is an angle of inclination with main flow.
Impact opening in described ribs is single row or multiple rows, and the diameter of described impact opening is millimeter magnitude.
Described fuel adopts fuel gas or liquid fuel.
The metal dust of micron dimension diameter and organic binder bond is adopted evenly to mix, under heating plasticizing state, solidified forming in die cavity is injected with injection machine after granulating, then by the method for chemistry or thermal decomposition, the binding agent in shaping base is removed, and obtain final products through sintering densification.
The present invention is owing to taking above technical scheme; it has the following advantages: 1, the inventive method is according to the characteristic of porous media; prop up on plate material in spray and produce multi-pore structure; utilize the concept of Sweat coolling, not only can realize the better blending of fuel and main flow, and fuel is served as cooling agent and complete Thermal protection to spray support plate outer surface; its cooling capacity is very large; from thermo-lag angle, only need lower fuel quantity, just can meet cooling needs.2, spray of the present invention props up intralamellar part owing to there is a large amount of holes, and specific area is very large, and therefore flow in fuel with spray support plate, strong heat convection occurs in the process of spray support plate, effectively can absorb the heat of solid, reduces spray and props up plate temperature.3, the present invention's speed of penetrating into main flow by the hole on spray support plate due to fuel is slower; therefore a thin layer can be formed on spray support plate surface; hinder the heat transfer on high temperature main flow and spray support plate surface; realize the protection to spray support plate especially its leading edge portion; prevent the ablative degradation 4 of spray support plate, the present invention owing to increasing ribs in spray support plate chamber; share stressed the produced tension in spray support plate both sides; therefore can increase the structural strength of spray support plate, make up the strength reduction adopting loose porous gap medium making spray support plate to bring.5, the present invention owing to making single or arranging impact opening more in ribs, and cartridge is communicated with the rear cavity of spray support plate, make fuel under pressure, while forward and backward cavity oozes out from the concrete dynamic modulus of wall, from rear cavity through ribs impact opening injection, be injected in front cavity inner surface, with on front cavity inner surface, strong heat convection occur, strengthen the cooling situation improving spray support plate leading edge portion further.6, the present invention is owing to being arranged to diamond structure by spray support plate, therefore can regulate spray support plate and the inclination angle carrying out flow path direction according to actual needs, main flow is weakened in the stagnation effect on spray support plate surface, improve thermal protection effect further.7, according to flight demand, the present invention can also on the basis of spray support plate of the present invention, be the nozzle opening of about 0.5mm size with the prior art perforate footpath on spray support plate that coexists mutually, increasing fuel injection rate, further raising cooling effectiveness, and prior art can not be there is concrete dynamic modulus Problems existing is not set.8, the inventive method props up plate structure owing to adopting the powder of stainless steel of 90 microns to sinter the mushy spray of making, therefore the spray support plate inside configuration made defines many micron dimension holes, porosity ensures at about 20%-30%, spray support plate intensity can be ensured while permission fuel flows through from micropore, bear certain fuel inlet pressure.The present invention can be widely used in various punching engine spray and prop up in the thermal protection of plate structure.
Accompanying drawing explanation
Fig. 1 is super burn engine structure schematic diagram
Fig. 2 is spray support plate scheme of installation of the present invention
Fig. 3 is spray support plate operation principle schematic diagram of the present invention
Fig. 4 is rhombus spray support plate structural representation of the present invention
Fig. 5 is the cross-sectional schematic of Fig. 4
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is described in detail.
As shown in Figure 1 and Figure 2, in super burn engine, be generally the different flight Mach number scopes according to aircraft, select aviation kerosine or liquid hydrogen as fuel, under some particular job environment, the employing fuel gas also had.Fuel is by the self-contained pump of super burn engine and the Valve controlling that is arranged on fuel channel, after arriving certain pressure, spray support plate 2 is entered by a cartridge 1, and spray according in the nozzle opening of designing requirement setting from spray support plate 2, main flow blending after-combustion with high-temperature high-speed airflow, provides power.The inventive method is structurally substantially identical with prior art; unlike the present invention to the improvement on spray support plate materials and structures; the inventive method, according to the characteristic of porous media, utilizes the concept of Sweat coolling, fuel is served as cooling agent and completes Thermal protection to spray support plate outer surface.
As shown in Figure 3, overall structure shape and the prior art of the spray support plate 2 of the inventive method are similar, comprise the stripe shape cavity that a front portion is gradually-reducing shape, one end of cavity is blind end, the other end to be connected super burn engine by a lower bottom base 3 upper bed-plate 4 with one is tightly connected, and is sealed by a sealing steel plate 5 and be communicated with cartridge 1.The principal character of the inventive method comprises: the wall surface material of spray support plate 2 is arranged to multi-cellular structure by first, and namely on the wall of whole spray support plate 2, be covered with micropore, fuel can under pressure, ooze out from micropore; Second increases the ribs 6 arranging a Steel material or other high temperature resistant solid material making in the cavity of spray support plate 2, spray support plate 2 is made to form former and later two cavitys 7,8, to share the tensile stress of the stressed generation in spray support plate 2 both sides, effectively increase the intensity of spray support plate 2; 3rd makes single or many rows diameter in ribs 6 is millimeter magnitude and is communicated with the impact opening 9 of forward and backward cavity; The 4th rear cavity 8 cartridge 1 being communicated with spray support plate 2, make fuel under pressure, while front cavity 7, rear cavity 8 ooze out from the micropore of wall, penetrate from the impact opening 9 of rear cavity 8 through ribs 6, be injected in front cavity 7 inner surface, while strong heat convection occurs front cavity 7 inner surface, fuel under pressure, oozes out in the concrete dynamic modulus of the past cavity 7 wall.
The spray support plate 2 of multi-cellular structure of the present invention can adopt the various exotic material of prior art and various different processing technology to obtain, such as: adopt the metal dust of micron dimension diameter (such as 90 microns) and organic binder bond evenly to mix, under heating plasticizing state, solidified forming in die cavity is injected with injection machine after granulating, then by the method for chemistry or thermal decomposition, the binding agent in shaping base is removed, and obtain final products through sintering densification.The spray support plate wall that the present invention is made by this many micropores manufacture craft defines many micron dimension holes, and porosity can ensure at about 20%-30%, and making precision is high, micropore even tissue, excellent performance.
In above-described embodiment, because spray support plate 2 is usually designed to forward edge line and main flow, to carry out flow path direction vertical, due to the stagnation effect in leading edge portion main flow, flow velocity is zero, static pressure static temperature is maximum, be unfavorable for that fuel oozes out while thermal environment is severe, therefore larger to the thermal protection difficulty of spray support plate 2.As shown in Figure 4, Figure 5, spray support plate 2, in order to address this problem, is designed to the diamond structure tilted by the present invention, makes the incline direction of spray support plate 2 leading edge and carry out flow path direction in an acute angle.Like this; under some particular job environment; as aircraft adopts fuel gas, fluid ratio thermal capacitance is little, and main flow flow velocity, Aerodynamic Heating amount are high especially; in the situations such as spray support plate 2 leading edge portion deathtrap cooling capacity is not enough; the spray support plate 2 of this diamond structure is adopted to design, can when main flow arrive leading edge portion, fluid still can flow along spray support plate 2 outer surface; thus weaken the stagnation effect of main flow, be conducive to improving the protection to spray support plate 2 leading edge hazardous part.
In above-described embodiment, in order to improve fuelcarrying charge, can also some nozzle openings offering about 0.5mm same as the prior art on spray support plate 2 as required, but due to the existence of multi-cellular structure of the present invention, spray support plate 2 will clearly alleviate prior art Problems existing.
The various embodiments described above are only for illustration of the present invention; wherein the manufacture craft, contour structures etc. of spray support plate all can change to some extent; every equivalents of carrying out on the basis of technical solution of the present invention and improvement, all should not get rid of outside protection scope of the present invention.
Claims (10)
1. utilize sweating and impinging cooling to a thermal protection method for super burn engine spray support plate, it comprises following content:
1) the spray support plate of multi-cellular structure is produced with exotic material, the ribs that one is divided into front cavity and rear cavity is set in spray support plate, ribs is provided with the impact opening being communicated with forward and backward cavity, by the rear cavity connects of the cartridge of super burn engine and spray support plate;
2) fuel is utilized to ooze out the process of multi-cellular structure spray support plate hole, heat convection is carried out in pressure, take away the heat on spray support plate surface, and utilize fuel to ooze out at spray support plate surface formation thin layer, intercept the main flow of high-temperature high-speed airflow to the heat transfer of spray support plate;
3) utilize fuel to be ejected into front cavity inner surface from the impact opening of rear cavity through ribs, carry out heat convection with front cavity inner surface, utilize the ribs in spray support plate to strengthen the intensity of spray support plate simultaneously.
2. utilize sweating and impinging cooling to the thermal protection method of super burn engine spray support plate as claimed in claim 1, it is characterized in that: the nozzle opening described spray support plate offering some 0.5mm.
3. utilize sweating and impinging cooling to the thermal protection method of super burn engine spray support plate as claimed in claim 1, it is characterized in that: the outer shape of described spray support plate is carry out the rhombus that flow path direction is an angle of inclination with main flow.
4. utilize sweating and impinging cooling to the thermal protection method of super burn engine spray support plate as claimed in claim 2, it is characterized in that: the outer shape of described spray support plate is carry out the rhombus that flow path direction is an angle of inclination with main flow.
5. as claimed in claim 1 or 2 or 3 or 4 utilize sweating and impinging cooling to the thermal protection method of super burn engine spray support plate, it is characterized in that: the impact opening in described ribs is single row or multiple rows, and the diameter of described impact opening is millimeter magnitude.
6. as claimed in claim 1 or 2 or 3 or 4 utilize sweating and impinging cooling to the thermal protection method of super burn engine spray support plate, it is characterized in that: described fuel adopts fuel gas or liquid fuel.
7. utilize sweating and impinging cooling to the thermal protection method of super burn engine spray support plate as claimed in claim 5, it is characterized in that: described fuel adopts fuel gas or liquid fuel.
8. as described in claim 1 or 2 or 3 or 4 or 7, utilize sweating and impinging cooling to the thermal protection method of super burn engine spray support plate, it is characterized in that: the metal dust and the organic binder bond Homogeneous phase mixing that adopt micron dimension diameter, under heating plasticizing state, solidified forming in die cavity is injected with injection machine after granulating, then by the method for chemistry or thermal decomposition, the binding agent in shaping base is removed, and obtain spray support plate through sintering densification.
9. utilize sweating and impinging cooling to the thermal protection method of super burn engine spray support plate as claimed in claim 5, it is characterized in that: the metal dust and the organic binder bond Homogeneous phase mixing that adopt micron dimension diameter, under heating plasticizing state, solidified forming in die cavity is injected with injection machine after granulating, then by the method for chemistry or thermal decomposition, the binding agent in shaping base is removed, and obtain spray support plate through sintering densification.
10. utilize sweating and impinging cooling to the thermal protection method of super burn engine spray support plate as claimed in claim 6, it is characterized in that: the metal dust and the organic binder bond Homogeneous phase mixing that adopt micron dimension diameter, under heating plasticizing state, solidified forming in die cavity is injected with injection machine after granulating, then by the method for chemistry or thermal decomposition, the binding agent in shaping base is removed, and obtain spray support plate through sintering densification.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310561173.6A CN103615741B (en) | 2013-11-12 | 2013-11-12 | Heat protection method for injection support plate of scramjet engine by utilizing sweat and impingement cooling |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310561173.6A CN103615741B (en) | 2013-11-12 | 2013-11-12 | Heat protection method for injection support plate of scramjet engine by utilizing sweat and impingement cooling |
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| CN103615741A CN103615741A (en) | 2014-03-05 |
| CN103615741B true CN103615741B (en) | 2015-05-20 |
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Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104633709A (en) * | 2014-12-11 | 2015-05-20 | 清华大学 | Thermal protection method of porous medium jetting support plate leading edge nose cone |
| EP3076084B1 (en) * | 2015-03-30 | 2021-04-28 | Ansaldo Energia Switzerland AG | Fuel injector device |
| CN104859835B (en) * | 2015-04-27 | 2017-06-16 | 清华大学 | A kind of hypersonic aircraft nose cone based on Compound cooling mode |
| CN106247407A (en) * | 2016-08-15 | 2016-12-21 | 西北工业大学 | A kind of fuel support plate ejector filler |
| CN109774981B (en) * | 2019-01-28 | 2020-07-03 | 清华大学 | Thermal protection system of auxiliary rocket of hypersonic vehicle |
| CN110425571B (en) * | 2019-07-23 | 2021-02-19 | 哈尔滨工业大学 | Three-column fuel supply structure for scramjet engine of hypersonic aircraft |
| CN110425572B (en) * | 2019-07-23 | 2021-02-19 | 哈尔滨工业大学 | Porous single-column fuel supply structure for supersonic aircraft ramjet engine |
| CN110701637B (en) * | 2019-09-20 | 2021-02-12 | 清华大学 | Compound combustion chamber thermal protection wall surface structure |
| CN110566999B (en) * | 2019-09-20 | 2020-07-28 | 清华大学 | Combustion chamber thermal protection wall surface structure utilizing fuel oil self-suction sweating cooling |
| CN112682993A (en) * | 2020-12-30 | 2021-04-20 | 北京动力机械研究所 | Water-cooling heat protection panel of heater |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4439980A (en) * | 1981-11-16 | 1984-04-03 | The United States Of America As Represented By The Secretary Of The Navy | Electrohydrodynamic (EHD) control of fuel injection in gas turbines |
| US5280705A (en) * | 1992-06-22 | 1994-01-25 | General Electric Company | Fuel injection system for scramjet engines |
| JP3192864B2 (en) * | 1994-03-30 | 2001-07-30 | 三菱重工業株式会社 | Fine fuel injection nozzle |
| FR2750169B1 (en) * | 1996-06-24 | 1998-08-21 | Aerospatiale | FUEL INJECTION DEVICE FOR A STATOREACTOR OPERATING AT A HIGH NUMBER OF MACH |
| US6463739B1 (en) * | 2001-02-05 | 2002-10-15 | General Electric Company | Afterburner heat shield |
| US20060191268A1 (en) * | 2005-02-25 | 2006-08-31 | General Electric Company | Method and apparatus for cooling gas turbine fuel nozzles |
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