CN109408993B - Design method of turbofan and ramjet combined engine with rocket inside - Google Patents
Design method of turbofan and ramjet combined engine with rocket inside Download PDFInfo
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Abstract
Design of turbofan and ramjet combined engine with rocket internally arranged in culvertThe method belongs to the field of combined engines, firstly, the overall performance requirement of the engine is formulated, a basic flow field of an air inlet channel is designed, and then a three-dimensional inward-turning air inlet channel is obtained by streamline tracing; obtaining the inlet and outlet parameters of the scramjet combustion chamber according to the overall performance of the engine, and designing the scramjet combustion chamber at the outlet of the three-dimensional inward-rotation air inlet channel; based on the parameters of the super-combustion chamber and the engine in the range of Ma4.5-6+Designing a tail nozzle with adjustable geometric area at the outlet of the scramjet combustion chamber according to the thrust requirement of the stage; selecting a turbofan engine based on the performance requirements of the engine in the Ma 0-2 stage, and arranging a turbofan-sub-combustion combined channel and the turbofan engine at an opening on the upper wall surface of a three-dimensional inward-rotation air inlet channel; arranging a rocket engine in a culvert channel of the turbofan engine; based on the thrust requirement of the Ma 0-5 state engine, the performance parameters of the Ma 0-2 state turbofan engine and the Ma 2-3 state rocket engine are combined, and a sub-combustion chamber with a convertible working mode is designed behind the turbofan engine.
Description
Technical Field
The invention relates to the field of combined engines, in particular to a design method of a turbofan ramjet combined engine with a built-in rocket in a culvert.
Background
Hypersonic flight is considered as a third revolution following propeller and jet propulsion, and the research on hypersonic aircraft technology is paid great attention to by major military matters in the world, including the united states. At present, the research of a combined power system which can realize horizontal takeoff and self-acceleration to hypersonic speed is turning from the research of a scramjet engine to the research of a combined power system, wherein the research is focused on the research of a turbine-based combined cycle engine. The turbine-based combined cycle engine (TBCC) is a power device formed by combining a turbine engine and other types of engines, is one of key power systems for realizing autonomous acceleration, powered horizontal landing and repeated use of a hypersonic aircraft, has the advantages of flexible launching and landing places, high durability, high unit thrust, capability of adopting common fuel and lubricant, low operation cost, high safety and the like, and is one of hypersonic power promising in the future.
The working Mach number of the turbine engine at the present stage is mainly Mach 0-2, and the working Mach number of the ramjet engine is Ma 3-6+In the Mach 2-3 range, the TBCC power systemThe problems that the working Mach number of a turbine engine cannot be increased and the working Mach number of a ramjet engine cannot be increased exist, the thrust of a combined engine in the mode conversion process cannot meet the thrust requirement of an aircraft, and the combined engine falls into a thrust gap which cannot be exceeded easily; in addition, the prior turbine engine mainly adopts a turbofan engine structure form, and an afterburner chamber of the turbofan engine is a sub-combustion chamber in nature.
Disclosure of Invention
The invention aims to solve the problems in the prior art, and provides a design method of a turbofan and ramjet combined engine containing a built-in rocket, which can keep the advantages of wide-speed-range flight and high specific impulse, simultaneously realize coexistence of two modal combustion chambers, improve the overall performance of a propulsion system, and has the advantages of simple and reliable structure, moderate technical difficulty and the like.
In order to achieve the purpose, the invention adopts the following technical scheme:
a design method of a turbofan ramjet combined engine with a built-in rocket in a culvert comprises the following steps:
1) the method comprises the steps that the overall performance requirement of an engine is made according to a flight task, an air inlet basic flow field is designed based on the overall performance requirement, and then a three-dimensional inward-turning air inlet is obtained by carrying out streamline tracing in the basic flow field;
2) obtaining the parameters of an inlet and an outlet of a super-combustion chamber according to the overall performance of the engine, and designing the super-combustion chamber at the outlet of the three-dimensional inward-rotation air inlet channel in the step 1);
3) based on the parameters of the scramjet combustion chamber in the step 2) and the engine in the range of Ma4.5-6+Designing a tail nozzle with adjustable geometric area at the outlet of the scramjet combustion chamber according to the thrust requirement of the stage, and designing a lower adjusting plate of the tail nozzle according to different working states of the tail nozzle;
4) selecting a turbofan engine based on Ma 0-2 stage engine performance requirements, and utilizing a flow formula according to the flow requirements
Calculating the inlet area of the combined turbofan-sub-combustion channel, wherein
Representing flow, rho representing density, A representing area, v representing inlet speed, and further arranging a turbofan-sub-combustion combined channel and a turbofan engine at the upper wall surface opening of the three-dimensional inward turning air inlet channel in the step 1);
5) arranging rocket engines with corresponding sizes in the bypass channel of the turbofan engine in the step 4) based on the thrust requirement of the engine in the Ma 2-3 stage to form an ejection rocket channel;
6) based on the thrust requirement of a Ma 0-5 state engine, combining the turbofan engine in the Ma 0-2 state step 4) and the rocket engine performance parameters in the Ma 2-3 state step 5), designing a sub-combustion chamber with a convertible working mode behind the turbofan engine in the step 4), wherein the average Mach number of an inlet of the sub-combustion chamber is not more than 0.25;
7) according to parameters such as outlet temperature, pressure and flow of the sub-combustion combustor in the step 6), arranging a turbine channel outlet throat adjustable device at the upper wall surface opening of the tail nozzle in the step 3), wherein the area of the turbine channel outlet throat ensures that all the flow passes under the Mach number state of each incoming flow;
8) the inlet splitter plate is hinged at the inlet of the turbofan-sub combustion combined channel to open or close the inlet of the turbofan-sub combustion combined channel;
9) an upper nozzle adjusting plate is hinged to the outlet end of the adjustable throat and can rotate to open or close the outlet of the turbofan-sub-combustion combined channel.
The turbofan ramjet combined engine with the rocket inside the culvert designed by the design method comprises a three-dimensional inward-turning air inlet channel, a turbofan-sub-combustion combined channel, a scramjet channel and a tail nozzle;
the three-dimensional inward-rotation air inlet channel is provided with a first outlet and a second outlet;
the tail nozzle is provided with a first inlet and a second inlet;
the inlet of the turbofan-sub-combustion combined channel is connected with the first outlet, and the outlet of the turbofan-sub-combustion combined channel is connected with the first inlet of the tail nozzle; a turbofan engine and a sub-combustion chamber are sequentially arranged in the turbofan-sub-combustion combined channel from an inlet to an outlet; the turbofan engine is arranged at one end of an inlet of the turbofan-sub combustion combined channel, and the sub combustion chamber is arranged at one end of an outlet of the turbofan-sub combustion combined channel; the turbofan engine is provided with a culvert channel and an inner culvert channel, and the rocket engine is arranged in the culvert channel in an inserting plate mode;
the inlet of the scramjet channel is connected with the second outlet, and the outlet of the scramjet channel is connected with the second inlet of the tail nozzle; and a super-combustion chamber is arranged in the super-combustion stamping channel.
The engine also comprises an air inlet splitter plate, an adjustable throat, an upper nozzle adjusting plate and a lower nozzle adjusting plate; the air inlet splitter plate is hinged to a first outlet of the three-dimensional inward-rotation air inlet so as to open or close an inlet of the turbofan-sub-combustion combined channel; the adjustable throat is arranged at a first inlet of the tail nozzle; the outlet end of the adjustable throat is hinged with an upper adjusting plate of the spray pipe, and the upper adjusting plate of the spray pipe can rotate to open or close the outlet of the turbofan-sub combustion combined channel; the lower nozzle adjusting plate is mounted at the second inlet of the tail nozzle and can move up and down to adjust the area of the tail nozzle.
The working principle of the invention is as follows:
1. the three-dimensional inward-rotation air inlet channel is provided with two outlets, the first outlet is connected with the turbofan-sub-combustion combined channel, the second outlet is connected with the super-combustion stamping channel, and the turbofan-sub-combustion combined channel and the super-combustion stamping channel are connected through two inlets and share the tail nozzle.
2. When the flight Mach number is 0-2, the turbofan-sub-combustion combined channel is opened, the turbofan engine and the sub-combustion chamber serving as the afterburner of the turbofan engine are ignited to work, the turbofan-sub-combustion combined channel is in the working mode of the turbofan engine, and the scramjet channel is not ignited and is in a flow discharge state.
3. When the flight Mach number is 2-3, the turbofan engine is closed and in a windmill state, the rocket engine is ignited to work, the sub-combustion chamber keeps burning, the turbofan-sub-combustion combined channel is in a working mode of ejecting the rocket sub-combustion ramjet engine, and the super-combustion ramjet channel plays a role in flow discharge.
4. When the flight Mach number is 3-4.5, the rocket engine stops working, the sub-combustion chamber keeps burning, the turbofan-sub-combustion combined channel is in a sub-combustion ramjet working mode, and the super-combustion chamber in the super-combustion ramjet channel ignites to work.
5. When the flight Mach number is 4.5-6+When the combined type scramjet nozzle is used, the air inlet splitter plate and the adjusting plate on the jet pipe rotate to close the turbofan-sub combustion combined channel, and a scramjet combustion chamber in the scramjet channel keeps burning.
Compared with the prior art, the technical scheme of the invention has the following beneficial effects:
1. the invention forms power hybrid (turbine/ram/rocket) by placing the rocket engine in the outer duct of the turbofan engine, combines the afterburner of the turbofan engine and the combustion chamber of the sublagration ramjet engine, and when the rocket engine and the sublagration ramjet engine work together in the same duct, the total thrust is larger than the sum of the two independent works due to the injection effect, thereby effectively spanning the thrust gap and reducing the complexity of the three-power combined system.
2. The invention integrates the advantages of high specific impulse of the turbofan engine, high Mach number of the ramjet engine and the full speed domain of the rocket engine, realizes the coexistence of two modal combustion chambers and improves the overall performance of the propulsion system.
3. The turbofan engine and the ejection rocket sub-combustion ramjet engine share one set of sub-combustion chamber and tail jet pipe, so that compared with a conventional three-channel and three-power combined engine, the structure of one set of sub-combustion chamber and tail jet pipe can be reduced, and the turbofan engine has the advantages of simple and reliable structure and moderate technical difficulty.
4. The rocket engine solves the problem that both the turbofan engine and the ramjet engine cannot generate enough thrust when Ma 2-3 is performed, and plays a role in ensuring the continuity of the thrust; the scramchannel and the scramjet combustor ensure that the combined engine has Ma4.5-6 under high Mach number+Aircraft/power system thrust balancing (i.e., at supersonic combustor inlet conditions).
Drawings
FIG. 1 is a schematic view of the overall structure of a turbofan ramjet combined engine incorporating a built-in rocket;
FIG. 2 is a schematic view of the internal structure of a turbofan ramjet combined engine with a rocket inside;
FIG. 3 is a schematic sectional view of the opening of the combined turbofan-sub-combustion channel;
FIG. 4 is a schematic cross-sectional view of the combined turbofan-sub-combustion channel shut-off;
FIG. 5 is a schematic diagram of the working principle of the present invention;
FIG. 6 is a partially enlarged view of the plane of the combined turbofan and sub-combustion channel.
The reference numbers 1 three-dimensional internal-rotation air inlet channel, 2 external-bypass channel, 3 internal-bypass channel, 4 overfire ram channel, 5 tail nozzle, 6 rocket engine, 7 turbofan engine core engine, 8 turbofan engine fan, 9 nozzle lower adjusting plate, 10 nozzle upper adjusting plate, 11 sub-combustion chamber, 12 turbofan-sub-combustion combined channel, 13 air inlet splitter plate, 14 overfire combustion chamber, 15 adjustable throat, 16 first outlet, 17 second outlet, 18 first inlet, 19 second inlet, ① and ② represent the position of the air inlet splitter plate in different working states of the engine, ③ and ④ represent the position of the nozzle lower adjusting plate in different working states of the overfire combustion chamber, ⑤ and ⑥ represent the position of the adjusting plate on the nozzle in different working states of the overfire combustion chamber, and ⑦ and ⑧ represent the position of adjustable throat adjustment of the sub-combustion chamber in different working states.
Detailed Description
In order to make the technical problems, technical solutions and advantageous effects of the present invention clearer, the present invention is described in further detail below with reference to the accompanying drawings and embodiments.
A design method of a turbofan ramjet combined engine with a built-in rocket in a culvert comprises the following steps:
1) the method comprises the steps that the overall performance requirement of an engine is made according to a flight task, an air inlet basic flow field is designed based on the overall performance requirement, and then a three-dimensional inward-turning air inlet is obtained by carrying out streamline tracing in the basic flow field;
2) obtaining the parameters of an inlet and an outlet of a super-combustion chamber according to the overall performance of the engine, and designing the super-combustion chamber at the outlet of the three-dimensional inward-rotation air inlet channel in the step 1);
3) based on the parameters of the scramjet combustion chamber in the step 2) and the engine in the range of Ma4.5-6+Designing a tail nozzle with adjustable geometric area at the outlet of the scramjet combustion chamber according to the thrust requirement of the stage, and designing a lower adjusting plate of the tail nozzle according to different working states of the tail nozzle;
4) selecting a turbofan engine based on Ma 0-2 stage engine performance requirements, and utilizing a flow formula according to the flow requirements
Calculating the inlet area of the combined turbofan-sub-combustion channel, wherein
Representing flow, rho representing density, A representing area, v representing inlet speed, and further arranging a turbofan-sub-combustion combined channel and a turbofan engine at the upper wall surface opening of the three-dimensional inward turning air inlet channel in the step 1);
5) arranging rocket engines with corresponding sizes in the bypass channel of the turbofan engine in the step 4) based on the thrust requirement of the engine in the Ma 2-3 stage to form an ejection rocket channel;
6) based on the thrust requirement of a Ma 0-5 state engine, combining the turbofan engine in the Ma 0-2 state step 4) and the rocket engine performance parameters in the Ma 2-3 state step 5), designing a sub-combustion chamber with a convertible working mode behind the turbofan engine in the step 4), wherein the average Mach number of an inlet of the sub-combustion chamber is not more than 0.25;
7) according to parameters such as outlet temperature, pressure and flow of the sub-combustion combustor in the step 6), arranging a turbine channel outlet throat adjustable device at the upper wall surface opening of the tail nozzle in the step 3), wherein the area of the turbine channel outlet throat ensures that all the flow passes under the Mach number state of each incoming flow;
8) the inlet splitter plate is hinged at the inlet of the turbofan-sub combustion combined channel to open or close the inlet of the turbofan-sub combustion combined channel;
9) an upper nozzle adjusting plate is hinged to the outlet end of the adjustable throat and can rotate to open or close the outlet of the turbofan-sub-combustion combined channel.
As shown in fig. 1 to 5, the turbofan ramjet combined engine with a culvert built-in rocket, which is designed by the design method of the invention, comprises a three-dimensional inward-turning air inlet channel 1, a turbofan-sub-combustion combined channel 12, an overfire ramjet channel 4, a tail nozzle 5, an air inlet channel splitter plate 13, an adjustable throat 15, an upper nozzle adjusting plate 10, a lower nozzle adjusting plate 9 and a rocket engine 6.
The three-dimensional inward-turning air inlet channel 1 is provided with a first outlet 16 and a second outlet 17.
The jet nozzle 5 is provided with a first inlet 18 and a second inlet 19.
The inlet of the turbofan-sub-combustion combined channel 12 is connected with a first outlet 16, and the outlet of the turbofan-sub-combustion combined channel 12 is connected with a first inlet 18 of the tail nozzle 5; the turbofan engine and the sub-combustion chamber 11 are sequentially arranged in the turbofan-sub-combustion combined channel 12 from an inlet to an outlet, the turbofan engine comprises a front turbofan engine fan 8 and a rear turbofan engine core 7, the turbofan engine is arranged at one end of the inlet of the turbofan-sub-combustion combined channel 12, and the sub-combustion chamber 11 is arranged at one end of the outlet of the turbofan-sub-combustion combined channel 12.
The inlet of the scramjet channel 4 is connected with a second outlet 17, and the outlet of the scramjet channel 4 is connected with a second inlet 19 of the tail pipe 5; the scramjet channel 4 is internally provided with a scramjet combustion chamber 14.
As shown in figures 2-6, the turbofan engine is provided with a culvert channel 2 and a culvert channel 3, and the rocket engine 6 is arranged in the culvert channel 2 in an inserting plate mode.
The air inlet splitter plate 13 is hinged at the first outlet 16 of the three-dimensional inward-turning air inlet 1 to open or close the inlet of the turbofan-sub combustion combined channel 12.
The adjustable throat 15 is mounted at a first inlet 18 of the jet nozzle 5; the outlet end of the adjustable throat 15 is hinged with the upper adjusting plate 10 of the nozzle, and the upper adjusting plate 10 of the nozzle can rotate to open or close the outlet of the turbofan-sub combustion combined channel 12;
the nozzle lower adjustment plate 9 is installed at the second inlet 19 of the tail nozzle 5, and the nozzle lower adjustment plate 9 is movable up and down to adjust the area of the tail nozzle 5.
As shown in fig. 5, the working process and principle of the present invention are as follows:
1. when the flight mach number is 0-2, as shown in fig. 3 and 5, the air inlet splitter plate 13 in the three-dimensional inward-rotation air inlet channel 1 is positioned at the uppermost position of the first outlet 16, namely, the state ①, the upper adjusting plate 10 of the nozzle rotates downwards to be in an open state, namely, the state ⑤, at the moment, the turbofan-sub-combustion combined channel 12 is in an open state, so that the air flow passes through the turbofan-sub-combustion combined channel 12, at the moment, the turbofan engine and the sub-combustion chamber 11 serving as an afterburner chamber of the turbofan engine are ignited to work, and the scramjet channel 4 is not ignited and is in a flow discharge state;
2. when the flying mach number is 2-3, the positions of the air inlet splitter plate 13 and the adjusting plate 10 on the spray pipe are unchanged, the turbofan engine is in a windmill state, the rocket engine 6 is ignited and combusted, the sub-combustion chamber 11 continues to work, and the generated air flow is accelerated through the adjustable throat 15 and generates thrust;
3. when the flying Mach number is 3-4.5, the rocket engine 6 stops working, the sub-combustion chamber 11 independently works, the super-combustion chamber 14 ignites, and the super-combustion stamping channel 4 is in the state of the ignition combustion chamber;
4. when the flight Mach number is 4.5-6+When the method is used, as shown in fig. 4-5, the air inlet splitter plate 13 rotates downwards to a state ②, the upper adjusting plate 10 of the nozzle rotates upwards to a state ⑥, so that the turbofan-sub combustion combined channel 12 is closed, the rocket 6, the turbofan engine and the sub combustion chamber 11 stop working, the super combustion chamber 14 keeps a combustion state at the moment, air flow expands through the tail nozzle 5 to do work to generate thrust, the area of the tail nozzle is controlled by adjusting the lower adjusting plate 9 of the nozzle under different incoming flow Mach numbers, thrust requirements are further guaranteed, and the lower adjusting plate 9 of the nozzle is adjusted steplessly from a state ③ to a state ④ along with the increase of the incoming flow Mach numbers.
The invention not only solves the problems that the compression engine can not be started and can not generate enough thrust under the working condition of low Mach number, but also ensures that the combined power has enough thrust under the working condition of high Mach number by the independent design of the super-combustion chamber.
Claims (9)
1. A design method of a turbofan and ramjet combined engine with a built-in rocket in a culvert is characterized in that: the method comprises the following steps:
1) the method comprises the steps that the overall performance requirement of an engine is made according to a flight task, an air inlet basic flow field is designed based on the overall performance requirement, and then a three-dimensional inward-turning air inlet is obtained by carrying out streamline tracing in the basic flow field;
2) obtaining the parameters of an inlet and an outlet of a super-combustion chamber according to the overall performance of the engine, and designing the super-combustion chamber at the outlet of the three-dimensional inward-rotation air inlet channel in the step 1);
3) based on the parameters of the scramjet combustion chamber in the step 2) and the engine in the range of Ma4.5-6+Designing a tail nozzle with adjustable geometric area at the outlet of the scramjet combustion chamber according to the thrust requirement of the stage, and designing a lower adjusting plate of the tail nozzle according to different working states of the tail nozzle;
4) selecting a turbofan engine based on Ma 0-2 stage engine performance requirements, and utilizing a flow formula according to the flow requirements
Calculating the inlet area of the combined turbofan-sub-combustion channel, wherein
Representing flow, rho representing density, A representing area, v representing inlet speed, and further arranging a turbofan-sub-combustion combined channel and a turbofan engine at the upper wall surface opening of the three-dimensional inward turning air inlet channel in the step 1);
5) arranging rocket engines with corresponding sizes in the bypass channel of the turbofan engine in the step 4) based on the thrust requirement of the engine in the Ma 2-3 stage to form an ejection rocket channel;
6) based on the thrust requirement of the engine in the Ma 0-5 state, combining the turbofan engine in the Ma 0-2 state step 4) and the rocket engine performance parameters in the Ma 2-3 state step 5), designing a sub-combustion chamber with a convertible working mode behind the turbofan engine in the step 4), wherein the average Mach number of an inlet of the sub-combustion chamber is not more than 0.25.
2. The design method of the turbofan ramjet combination engine with built-in rocket in the outer culvert of claim 1, characterized in that: further comprising the steps of:
7) according to the outlet temperature, pressure and flow parameters of the sub-combustion combustor in the step 6), arranging a turbine channel outlet throat adjustable device at the upper wall surface opening of the tail pipe in the step 3), wherein the area of the turbine channel outlet throat ensures that all the flow passes under the Mach number state of each incoming flow.
3. The design method of the turbofan ramjet combination engine with built-in rocket in the culvert of claim 2, characterized in that: further comprising the steps of:
8) and the inlet splitter plate is hinged at the inlet of the turbofan-sub combustion combined channel to open or close the inlet of the turbofan-sub combustion combined channel.
4. The design method of the turbofan ramjet combination engine with the built-in rocket in the culvert as claimed in claim 3, characterized in that: further comprising the steps of:
9) an upper nozzle adjusting plate is hinged to the outlet end of the adjustable throat and can rotate to open or close the outlet of the turbofan-sub-combustion combined channel.
5. The utility model provides a turbofan punching press combination engine of built-in rocket of foreign culvert which characterized in that: the device comprises a three-dimensional inward-rotation air inlet channel, a turbofan-sub-combustion combined channel, an over-combustion stamping channel and a tail nozzle; the three-dimensional inward-rotation air inlet channel is provided with a first outlet and a second outlet; the tail spray pipe is provided with a first inlet and a second inlet; the inlet of the turbofan-sub-combustion combined channel is connected with the first outlet, and the outlet of the turbofan-sub-combustion combined channel is connected with the first inlet of the tail nozzle; a turbofan engine and a sub-combustion chamber are sequentially arranged in the turbofan-sub-combustion combined channel from an inlet to an outlet, the turbofan engine is provided with a culvert channel and an culvert channel, and the rocket engine is arranged in the culvert channel in a plug board manner; the inlet of the scramjet channel is connected with the second outlet, the outlet of the scramjet channel is connected with the second inlet of the tail nozzle, and a scramjet chamber is arranged in the scramjet channel; the three-dimensional internal rotation air inlet is hinged to the first outlet of the three-dimensional internal rotation air inlet, and the inlet of the turbofan-sub combustion combined channel is opened or closed.
6. The turbofan ramjet combination engine of a build-in rocket of claim 5, wherein: an adjustable throat is installed at the first inlet of the tail nozzle.
7. The turbofan ramjet combination engine of a build-in rocket of claim 6, wherein: the outlet end of the adjustable throat is hinged with an upper adjusting plate of the spray pipe, and the upper adjusting plate of the spray pipe can rotate to open or close the outlet of the turbofan-sub combustion combined channel.
8. The turbofan ramjet combination engine of a build-in rocket of claim 5, wherein: the lower nozzle adjusting plate is arranged at a second inlet of the tail nozzle and can move up and down to adjust the area of the tail nozzle.
9. The turbofan ramjet combination engine of a build-in rocket of claim 5, wherein: the turbofan engine is installed at one end of an inlet of the turbofan-sub combustion combined channel, and the sub combustion chamber is installed at one end of an outlet of the turbofan-sub combustion combined channel.
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| CN112948967B (en) * | 2021-02-08 | 2022-05-17 | 厦门大学 | Series-parallel three-power combined engine design method |
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| CN106837550B (en) * | 2017-02-06 | 2018-10-09 | 厦门大学 | The design method of hypersonic triple channel air intake duct |
| CN108561244B (en) * | 2017-12-29 | 2019-10-18 | 厦门大学 | The three power combination engine design methods that a kind of super burn and sub- combustion combustion chamber coexist |
| CN207920737U (en) * | 2017-12-29 | 2018-09-28 | 厦门大学 | A kind of three power combination engines with super burn Yu the double combustion chambers Ya Ran |
| CN209083430U (en) * | 2018-11-02 | 2019-07-09 | 厦门大学 | The turbofan punching press combined engine of rocket built in a kind of outer culvert |
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