CN113803164B - Ultra-miniature turbojet power device - Google Patents
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- CN113803164B CN113803164B CN202111087116.XA CN202111087116A CN113803164B CN 113803164 B CN113803164 B CN 113803164B CN 202111087116 A CN202111087116 A CN 202111087116A CN 113803164 B CN113803164 B CN 113803164B
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- 239000011229 interlayer Substances 0.000 claims abstract description 19
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- 235000012431 wafers Nutrition 0.000 claims abstract description 17
- 238000002347 injection Methods 0.000 claims abstract description 15
- 239000007924 injection Substances 0.000 claims abstract description 15
- 239000002737 fuel gas Substances 0.000 claims abstract description 14
- 238000005516 engineering process Methods 0.000 claims abstract description 12
- 229910021421 monocrystalline silicon Inorganic materials 0.000 claims abstract description 10
- 238000009792 diffusion process Methods 0.000 claims abstract description 8
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical group [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims abstract description 7
- 229910052710 silicon Inorganic materials 0.000 claims abstract description 7
- 239000010703 silicon Substances 0.000 claims abstract description 7
- 238000007789 sealing Methods 0.000 claims abstract description 3
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- 239000007789 gas Substances 0.000 claims description 19
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- 238000001816 cooling Methods 0.000 claims description 3
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- 238000005530 etching Methods 0.000 claims description 3
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- 238000004519 manufacturing process Methods 0.000 claims description 2
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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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
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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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
- F02C3/16—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- 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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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The invention discloses an ultra-miniature turbojet power device. The device comprises: the compressor rotor of the single-stage radial-flow compressor and the turbine rotor of the single-stage radial-flow turbine form an integral rotor; a microscale combustor is formed between the single-stage radial compressor and the single-stage centripetal turbine, the microscale combustor comprising: the annular fuel injection port, the annular cavity heat insulation interlayer and the flame tube with the protruding flaring are arranged to ensure that the fuel and the main flow are fully premixed and preheated, and the high-temperature high-pressure fuel gas flows into a turbine rotor of the turbine along the single-stage radial direction to do work and then is converted into axial discharge again; the turbojet power device is formed by adopting 6 monocrystalline silicon wafers with the thickness of 0.4mm, 2 monocrystalline silicon wafers with the thickness of 0.6mm and 3 monocrystalline silicon wafers with the thickness of 0.8mm to be singly etched and molded, and sealing adjacent silicon wafers into an airflow channel through a diffusion bonding connection technology. The invention can meet the urgent requirement of the micro unmanned aerial vehicle on the power-weight ratio of the power device, and has larger improvement potential in performance.
Description
Technical Field
The invention relates to the technical field of miniature turbine engines, in particular to an ultra-miniature turbine jet power device.
Background
The miniature unmanned plane (Micro Air Vehicle, MAV) has the characteristics of small volume, high speed, strong investigation capability, good concealment, simple operation, flexibility and the like, is used as a miniature reconnaissance machine in the military field for battlefield reconnaissance, target monitoring, target searching, signal interference, close combat, even reconnaissance of important sensitive parts of enemies and eavesdropping enemies in large-scale building facilities, and can also be used for detecting military dynamic tasks of dangerous areas which are not easy to reach or not easy to be interfered by human beings such as biochemical pollution areas, nuclear radiation dangerous areas and the like, so that an 'air eye' is added for a battlefield; in civil aspect, MAV mainly uses environmental monitoring, meteorological monitoring, forest fire prevention monitoring, flood disaster monitoring, still can be used to fields such as take photo by plane, crops monitoring, spraying pesticide. At present, the western military and the strong countries enter the research hot-tide stage of the micro unmanned aerial vehicle, but the micro unmanned aerial vehicle needs to be developed, and the most important and urgent core technology to be solved is the problem of the ultra micro power device with high energy density, so that the research of the novel ultra micro power device with high energy storage density, small volume, light weight and high power is urgent in developing the micro unmanned aerial vehicle.
The ultra-micro turbojet power plant (Ultra Micro Turbine Engine, UMTE) has the characteristics of high power density and high energy, and is a power plant with high energy density which is urgently needed by a micro unmanned aerial vehicle. According to the special thermal cycle and structural characteristics of UMTE, the power device needs to adopt a structural form of integrating a single-stage radial compressor, a micro-scale combustion chamber and a single-stage centripetal turbine, the number of parts and the number of connecting points are required to be as small as possible, the diameter of the whole device is not more than 22mm, and the axial length is not more than 6mm; the pressure ratio of the air flow in the single-stage compressor is not higher than 4, the tangential speed of the rotor reaches 500m/s, the residence time of the fuel gas in the combustion chamber is only 0.5ms, which is an order of magnitude lower than that of the air flow in the traditional combustion chamber, and the temperature of the fuel gas flowing into the turbine is not lower than 1500K.
Disclosure of Invention
The invention solves the technical problems that: overcomes the defects of the prior art and provides an ultra-miniature turbine power device.
In order to solve the above technical problems, an embodiment of the present invention provides an ultra-micro turbojet power device, including:
the device comprises: a single stage radial flow compressor, a microscale combustor, and a single stage centripetal turbine, wherein,
the compressor rotor of the single-stage radial flow compressor and the turbine rotor of the single-stage centripetal turbine form an integral rotor;
the microscale combustor is formed between the single-stage radial compressor and the single-stage centripetal turbine, and comprises: the annular fuel injection port, the annular cavity heat insulation interlayer and the flame tube with the protruding flaring are arranged to ensure that the fuel and the main flow are fully premixed and preheated, and the high-temperature high-pressure fuel gas flows into a turbine rotor of the turbine along the single-stage radial direction to do work and then is converted into axial discharge again;
the turbojet power device is formed by adopting 6 monocrystalline silicon wafers with the thickness of 0.4mm, 2 monocrystalline silicon wafers with the thickness of 0.6mm and 3 monocrystalline silicon wafers with the thickness of 0.8mm to be singly etched and molded, and sealing adjacent silicon wafers into an airflow channel through a diffusion bonding connection technology.
Optionally, the single-stage radial-flow compressor is composed of an air inlet channel, the compressor rotor, a compressor stator and a fuel injection port; wherein,,
the air inlet channel is arranged at the center of the compressor stator;
the compressor rotor is provided with a plurality of blades, so that the air flow passing through the air inlet channel flows along the radial direction after passing through the compressor rotor and then passes through the diffuser blades on the compressor stator to play a role of speed reduction and diffusion;
the fuel injection port is arranged on the section of the stator outlet of the compressor in an annular structure, and the circumferential direction is in a uniform multipoint form.
Optionally, the micro-scale combustion chamber consists of an annular cavity heat insulation interlayer, a flame tube, an ignition electric nozzle, a protruding flaring and a fuel gas outlet, wherein,
the annular cavity heat insulation interlayer is arranged on the outer side of the micro-scale combustion chamber in an annular cylinder shape so as to cool the wall of the combustion chamber and preheat the premixed gas;
the flame tube is characterized in that the air flow inlet of the flame tube is provided with the protruding flaring, the ignition electric nozzles are circumferentially arranged in the premise of the combustion chamber so as to ignite the tissue of the combustion chamber to burn, and then the flame tube flows into the single-stage centripetal turbine through the gas outlet.
Optionally, the single stage centripetal turbine is comprised of a turbine guide, a turbine rotor, and an exhaust port, wherein,
the turbine guide is provided with a plurality of guide blades, and after high-temperature airflow passes through the turbine guide, blades flowing into the turbine rotor in the radial direction drive the turbine rotor to do work, then turn by 90 degrees and are axially discharged from the annular exhaust passage.
Optionally, the outlet diameter of the compressor stator is 7mm, and the fuel injection port is circumferentially arranged at the outlet.
Optionally, the width of the annular cavity heat insulation interlayer is 0.4mm, and the axial length is 4.4mm.
Compared with the prior art, the invention has the advantages that:
the design inlet flow rate of the ultra-miniature turbojet power device is 0.35g/s, the thrust is 0.3N, the temperature before the turbine is 1500K, the urgent requirements of the miniature unmanned aerial vehicle on the power-weight ratio of the power device can be met, and meanwhile, the improvement potential in the aspect of performance is larger; and the ultra-miniature turbojet power device has compact structure, small size (diameter 22mm, length 6 mm) and light weight (4.2 g), and can meet the power structural requirement of a miniature unmanned aerial vehicle.
Drawings
FIG. 1 is a schematic view of an embodiment of an ultra-miniature turbojet power plant;
fig. 2 is a schematic structural diagram of a single-stage radial compressor according to an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a micro-scale combustor according to an embodiment of the present invention;
FIG. 4 is a schematic view of a single stage centripetal turbine according to an embodiment of the invention;
fig. 5 is a schematic structural diagram of an integral rotor according to an embodiment of the present invention.
Detailed Description
The scheme adopts a small-flow radial-flow high-pressure ratio air compressor, simultaneously arranges annular fuel injection points along the outlet flow passage of the air compressor in advance, and sets an annular cavity heat insulation interlayer outside the combustion chamber, so that injected fuel is premixed with a main flow as early as possible, premixed gas can be preheated, the mixing time is prolonged, uniformly distributed fuel gas is formed, and in addition, a sudden flaring is designed at the inlet of the combustion chamber to improve flame stability.
Next, the technical solutions of the embodiments of the present invention are described in detail below with reference to the drawings of the specification.
Referring to fig. 1, a schematic structural diagram of an femto-turbine jet power device according to an embodiment of the present invention is shown, and as shown in fig. 1, the femto-turbine jet power device may include: a single stage radial flow compressor 1, a micro-scale combustor 2, a single stage centripetal turbine 3 and an integral rotor 4.
As shown in fig. 1 to 5, the compressor rotor 1b of the radial compressor 1 and the turbine rotor 3b of the radial turbine 3 are designed as one integral rotor 4; a microscale combustion chamber 2 is designed between the radial compressor 1 and the centripetal turbine 3, the microscale combustion chamber 2 is designed into a flame tube 2b with an annular fuel injection port 1d, an annular cavity heat insulation interlayer 2a and a protruding flaring 2d, so as to ensure that fuel and main flow are fully premixed and preheated, prevent backfire, stabilize flame and prolong the residence time of fuel gas in the combustion chamber, and finally high-temperature and high-pressure fuel gas flows into the turbine 3 along the radial direction to drive a turbine rotor 3b to do work and then is converted into axial discharge again;
the single-stage radial-flow compressor 1 consists of an air inlet channel 1a, a compressor rotor 1b, a compressor stator 1c and a fuel injection port 1d; the air inlet 1a is arranged at the center of the compressor stator 1c, 20 blades 1b-1 with the blade height of 0.58mm are designed on the compressor rotor 1b, so that the air flow passing through the air inlet 1a flows along the radial direction after passing through the compressor rotor 1b, then the air flow passes through 13 diffuser blades 1c-1 with the blade height of 0.6mm designed on the compressor stator 1c for decelerating and diffusing, and meanwhile, 15 phi 0.3mm fuel injection ports 1d are uniformly arranged on the circumference of the section of the outlet R=7mm of the compressor stator 1b in order to ensure that the fuel is fully mixed in a limited space;
the micro-scale combustion chamber 2 consists of a combustion chamber heat insulation interlayer 2a, a flame tube 2b, an ignition electric nozzle 2c, a protruding flaring 2d and a fuel gas outlet 2 e; the combustion chamber interlayer 2a is 0.4mm wide and 4.4mm long, the annular cavity is arranged on the outer side of the combustion chamber 2 and plays roles in cooling the wall of the combustion chamber and preheating premixed gas, meanwhile, the air flow is more uniformly distributed after being premixed for 1.4ms in the annular cavity interlayer, the combustion chamber inlet is provided with a protruding flaring 2d which is 0.6mm wide, the purposes of stabilizing flame and prolonging the residence time of fuel gas are achieved, and 6 ignition electric nozzles 2c are uniformly arranged in the circumferential direction of the section R=9mm in the flame tube 2 b;
the single-stage centripetal turbine 3 is composed of a turbine guide 3a, a turbine rotor 3b and an exhaust port 3 c; wherein 24 guide blades 3a-1 with the blade height of 0.3mm are designed on the turbine guide 3a, after the high-temperature air flows into the guide 3a, 15 turbine rotor blades 3b-1 with the blade height of 0.27mm flow into the guide to drive the turbine rotor 3b to do work, then the guide blades are turned by 90 degrees again, and the guide blades are axially discharged from the annular exhaust passage 3 c.
The implementation process of the ultra-micro turbojet power device provided by the embodiment of the invention is given below, and the implementation process is specifically as follows:
step 1: according to the special thermal cycle and structural characteristics of UMTE, namely the flow rate is 0.35g/s, the fuel flow rate is 0.01g/s, the diameter is no more than 22mm, the axial length is 6mm, the tangential speed of a rotor is up to 500m/s, the gas temperature at the inlet of a turbine is not lower than 1500K, a single-stage radial compressor, a microscale combustion chamber and a single-stage centripetal turbine are adopted as a whole, the structure is limited by the structural size, the whole machine adopts a micro-electromechanical manufacturing (MEMS) technology, and a cavity, a fixed blade, a rotating blade, a fuel nozzle and an air inlet/outlet of the device are independently etched on a single-layer silicon wafer by adopting a semiconductor micro-etching technology, and then the single-layer silicon wafer layer and the layer are connected to form a whole by adopting a diffusion bonding technology.
Step 2: the air flow is rotated 90 degrees after flowing in from an air inlet and enters a runner with the height of 0.6mm under the attraction of 20 compressor rotor blades with the blade height of 0.58mm, the pressure ratio of the pressurized air of the air compressor reaches 4.0, and then the air flow is rotated 90 degrees after being subjected to speed reduction and diffusion through compressor diffuser blades (13 blades with the blade height of 0.6 mm) and flows into a combustion chamber;
step 3: in order to ensure that the fuel gas is fully mixed in a limited space, 15 phi 0.3mm fuel injection ports are uniformly designed in the circumferential direction of the section of the outlet R=7.0 mm of the stator of the compressor, so that the fuel is mixed with the main flow in advance;
step 4: an annular cavity heat insulation interlayer with the width of 0.4mm and the length of 4.4mm is designed at the position of the outermost side of the combustion chamber and the interval of 0.3mm between the combustion chamber and the flame tube, the air flow is further uniformly mixed in the annular cavity heat insulation interlayer, meanwhile, the cooling protection effect is achieved on the flame tube of the combustion chamber, then the air flow turns 180 degrees to enter a combustion chamber protruding flaring opening with the width of 0.6mm, the air flow speed passing through the protruding flaring opening is about 5.0m/s, 6 ignition electric nozzles are uniformly designed in the circumferential direction of the section with the R=9mm after the mixed gas flows into the combustion chamber, ignition tissues are combusted, and the mixed gas enters a turbine after staying for about 3.5 ms;
step 5: after the gas with the temperature of about 1500K is rectified and accelerated by 24 guide vanes with the vane height of 0.3mm, the gas flows into 15 turbine rotor vanes with the vane height of 0.27mm in the radial direction to drive the whole rotor to do work, and finally, the gas is axially discharged from an exhaust port by rotating 90 degrees, so that reverse thrust is generated.
The ultra-miniature turbojet power device provided by the embodiment of the invention is a micro-electro-mechanical etching technology based on monocrystalline silicon wafers, and by breaking through an integrated design method of a radial compressor, a micro-scale combustion chamber and a centripetal turbine, small-flow gas distribution is effectively organized, the geometric space of a small-size structure is reasonably arranged, and the requirements of high power, micro size and light miniature unmanned aerial vehicle power are met. The main advantages and effects are as follows:
1) The design inlet flow rate of the ultra-miniature turbojet power plant is 0.35g/s, the thrust is 0.3N, the temperature before the turbine is 1500K, the urgent requirement of the miniature unmanned aerial vehicle on the power weight ratio of the power plant can be met, and meanwhile, the improvement potential in the aspect of performance is larger;
2) The ultra-miniature turbojet power device has compact structure, small size (diameter 22mm, length 6 mm) and light weight (4.2 g), and can meet the power structural requirement of a miniature unmanned aerial vehicle.
The specific embodiments described herein will be described in order to provide a more thorough understanding of the present application to those skilled in the art, and are not intended to limit the present application in any way. Accordingly, it will be understood by those skilled in the art that the present application is still modified or equivalently substituted; all technical solutions and modifications thereof that do not depart from the spirit and technical essence of the present application are intended to be included in the protection scope of the present application.
What is not described in detail in the present specification is a well known technology to those skilled in the art.
Claims (1)
1. An ultra-miniature turbojet power plant, characterized in that it comprises: a single stage radial flow compressor, a microscale combustor, and a single stage centripetal turbine, wherein,
the microscale combustor is formed between the single-stage radial compressor and the single-stage centripetal turbine, and comprises: the flame tube with the annular fuel injection port, the annular cavity heat insulation interlayer and the protruding flaring is used for ensuring full premixing and preheating of fuel and main flow and improving combustion stability, and high-temperature and high-pressure fuel gas flows into the turbine along the single-stage radial direction to drive the turbine rotor to do work and then is converted into axial discharge again;
the turbojet power device is formed by adopting 6 monocrystalline silicon wafers with the thickness of 0.4mm, 2 monocrystalline silicon wafers with the thickness of 0.6mm and 3 monocrystalline silicon wafers with the thickness of 0.8mm to be singly etched and molded, and sealing adjacent silicon wafers into an airflow channel through a diffusion bonding connection technology;
the single-stage radial-flow compressor consists of an air inlet channel, a compressor rotor, a compressor stator and a fuel injection port; wherein,,
the air inlet channel is arranged at the center of the compressor stator;
the compressor rotor is provided with a plurality of blades, so that the air flow passing through the air inlet channel flows along the radial direction after passing through the compressor rotor and then passes through the diffuser blades on the compressor stator, and the diffuser blades are designed to be inclined curved surfaces;
the fuel injection port is arranged on the section of the stator outlet of the compressor in an annular structure, and the circumferential direction is in a uniform multipoint form;
the micro-scale combustion chamber consists of an annular cavity heat insulation interlayer, a flame tube, an ignition electric nozzle, a protruding flaring and a fuel gas outlet, wherein,
the annular cavity heat insulation interlayer is arranged on the outer side of the micro-scale combustion chamber in an annular cylinder shape so as to cool the wall of the combustion chamber and preheat the premixed gas;
a protruding flaring is arranged at the position of the air flow inlet of the flame tube, the width of the protruding flaring is 0.6mm, and a transverse flow passage is arranged between the annular cavity heat insulation interlayer and the protruding flaring;
a plurality of ignition nozzles are circumferentially arranged in the combustion chamber so as to ignite the combustion chamber tissue for combustion, and then flow into the single-stage centripetal turbine through the gas outlet;
the single-stage centripetal turbine consists of a turbine guide, a turbine rotor and an exhaust port, wherein,
the turbine guide is provided with a plurality of guide blades, after high-temperature airflow passes through the turbine guide, blades flowing into the turbine rotor in the radial direction drive the turbine rotor to do work, then the blades are turned by 90 degrees, and the high-temperature airflow is axially discharged from the annular exhaust passage;
the diameter of the outlet of the compressor stator is 7mm, and the fuel injection port is circumferentially arranged at the outlet;
the width of the annular cavity heat insulation interlayer is 0.4mm, and the axial length is 4.4mm;
the implementation method of the ultra-miniature turbojet power device comprises the following steps:
step 1: according to the special thermal cycle and structural characteristics of UMTE, namely the flow rate is 0.35g/s, the fuel flow rate is 0.01g/s, the diameter is no more than 22mm, the axial length is 6mm, the tangential speed of a rotor is up to 500m/s, the gas temperature at the inlet of a turbine is not lower than 1500K, a single-stage radial compressor, a microscale combustion chamber and a single-stage centripetal turbine are adopted to form an integrated structure, the structure is limited by the structural size, the whole machine adopts a micro-electromechanical manufacturing technology, the cavity, a fixed blade, a rotating blade, a fuel nozzle and an air inlet/outlet of the device are independently etched on a single-layer silicon wafer by adopting a semiconductor micro-etching technology, and a single-layer silicon wafer layer is connected with a layer by adopting a diffusion bonding technology to form the whole;
step 2: the air flow is rotated 90 degrees after flowing in from an air inlet under the attraction of 20 compressor rotor blades with the blade height of 0.58mm, enters a runner with the height of 0.6mm, has the pressure ratio of 4.0 after being pressurized, and then flows into a combustion chamber after being subjected to speed reduction and diffusion through a compressor diffuser blade, and is rotated 90 degrees again;
step 3: in order to ensure that the fuel gas is fully mixed in a limited space, 15 phi 0.3mm fuel injection ports are uniformly designed in the circumferential direction of the section of the outlet R=7.0 mm of the stator of the compressor, so that the fuel is mixed with the main flow in advance;
step 4: an annular cavity heat insulation interlayer with the width of 0.4mm and the length of 4.4mm is designed at the position of the outermost side of the combustion chamber and the interval of 0.3mm between the combustion chamber and the flame tube, the air flow is further uniformly mixed in the annular cavity heat insulation interlayer, meanwhile, the cooling protection effect is achieved on the flame tube of the combustion chamber, then the air flow turns 180 degrees to enter a combustion chamber protruding flaring opening with the width of 0.6mm, the air flow speed passing through the protruding flaring opening is about 5.0m/s, 6 ignition electric nozzles are uniformly designed in the circumferential direction of the section with the R=9mm after the mixed gas flows into the combustion chamber, ignition tissues are combusted, and the mixed gas enters a turbine after staying for about 3.5 ms;
step 5: after the gas with the temperature of about 1500K is rectified and accelerated by 24 guide vanes with the vane height of 0.3mm, the gas flows into 15 turbine rotor vanes with the vane height of 0.27mm in the radial direction to drive the whole rotor to do work, and finally, the gas is axially discharged from an exhaust port by rotating 90 degrees, so that reverse thrust is generated.
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| CN201053353Y (en) * | 2006-12-29 | 2008-04-30 | 深圳市康铖机械设备有限公司 | Mini turbine jet engine |
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| US6987329B1 (en) * | 2004-08-03 | 2006-01-17 | Harris Corporation | Fuel flexible thermoelectric micro-generator with micro-turbine |
| CN102878579B (en) * | 2012-10-11 | 2015-03-04 | 北京航空航天大学 | Rear-placed combustor with annular porous medium head for ultramicro turbojet engine |
| CN104088702B (en) * | 2014-07-01 | 2016-04-20 | 北京航空航天大学 | A kind of compact miniature gas turbine |
| CN104963775A (en) * | 2015-07-06 | 2015-10-07 | 北京理工大学 | Miniature type bladeless gas turbine |
| CN105066174A (en) * | 2015-07-24 | 2015-11-18 | 北京航空航天大学 | Super-micro turbojet engine combustor with inverted-L-shaped head |
| CN109057969A (en) * | 2018-08-08 | 2018-12-21 | 北京航空航天大学 | A kind of miniature gas turbine |
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Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201053353Y (en) * | 2006-12-29 | 2008-04-30 | 深圳市康铖机械设备有限公司 | Mini turbine jet engine |
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