CN112307558A - Three-dimensional curved surface flow guide channel, flame guide cabin and design method of flow guide channel - Google Patents
Three-dimensional curved surface flow guide channel, flame guide cabin and design method of flow guide channel Download PDFInfo
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Abstract
The invention provides a three-dimensional curved surface flow guide channel, a flame guide cabin and a design method of the flow guide channel, wherein the inlet of the flow guide channel at the front end of the flow guide channel is connected with the outlet of an aircraft spray pipe, and the rear end of the flow guide channel is connected with a booster; the flow guide channel comprises a central wedge, two groups of side plates, a top plate and a bottom plate, wherein the two groups of side plates, the top plate and the bottom plate are positioned on two sides of the wedge, the wedge is of a symmetrical V-shaped shell structure, the head part of the wedge is of a linear structure positioned at the inlet of the flow guide channel and divides the inlet of the flow guide channel into two parts, two wings of the wedge are of an outward convex cambered surface structure, the two wings are opened, the tail part of the wedge is of an arc structure and the wedge; two inner flow channels of the flow guide channel are respectively enclosed by the two wings and the side plate, the top plate and the bottom plate, and cold airflow and high-temperature gas enter the inner flow channels at the two sides through the divided flow guide channel inlets and are discharged. The three-dimensional outward-convex type central cone diversion channel structure can smoothly lead out cold airflow and high-temperature fuel gas of the aircraft spray pipe, remarkably improve mass flow rate and flow and reduce aircraft resistance.
Description
Technical Field
The invention belongs to the technical field of flow guide channel design, and particularly relates to a three-dimensional curved surface flow guide channel, a flame guide cabin and a flow guide channel design method.
Background
The air-breathing hypersonic aerocraft with booster generally adopts the mode of air inlet protective cover or diversion stage section in order to prevent the structure damage caused by the low-frequency pulsation of the air inlet of the aerocraft. If the power performance of the air-breathing engine is verified in the boosting section, the design of a flow guide stage section can be only adopted, so that the whole aircraft is in a through-flow state of an inner flow channel, and once the flow guide channel cannot normally guide flow under a cold condition to cause the blockage of the inner flow channel, incoming air inflow is influenced, and the engine cannot be started; after the engine is ignited (in a hot state), the flow guide channel is required to smoothly guide the jet flow of the engine, and once the jet flow cannot be guided out of the inner flow channel to cause blockage, the work of the engine is influenced.
The flow guide channel is of a special-shaped structure and is influenced by combined action of internal flow and external flow, a shock wave boundary layer in the flow channel has a complex interference flow phenomenon, separation vortex is easy to generate, and the risk of blockage exists, so that detailed optimization design needs to be carried out on the flow guide channel and the flow capacity of the flow guide channel.
Disclosure of Invention
In order to overcome the defects in the prior art, the inventor of the invention carries out intensive research and provides a three-dimensional curved surface flow guide channel and a design method thereof, so that the flow guide channel meets the requirements of cold and hot flow guide, namely, cold airflow and high-temperature gas of an aircraft spray pipe are smoothly guided out, and meanwhile, the requirements of the separation of the aircraft and a booster, the hot environment, the structure and the like are met, thereby completing the invention.
The technical scheme provided by the invention is as follows:
in a first aspect, a three-dimensional curved surface flow guide channel is provided, wherein a flow guide channel inlet at the front end of the flow guide channel is connected with an outlet of an aircraft spray pipe, and the rear end of the flow guide channel is connected with a booster;
the flow guide channel comprises a central wedge, two groups of side plates, a top plate and a bottom plate, wherein the two groups of side plates, the top plate and the bottom plate are positioned on two sides of the wedge, the wedge is of a symmetrical V-shaped shell structure, the head part of the wedge is of a linear structure positioned at the inlet of the flow guide channel and divides the inlet of the flow guide channel into two parts, two wings of the wedge are of an outward convex cambered surface structure, the two wings are opened, the tail part of the wedge is of an arc structure and the wedge; two inner flow channels of the flow guide channel are respectively enclosed by the two wings and the side plate, the top plate and the bottom plate, and cold airflow and high-temperature gas enter the inner flow channels at the two sides through the divided flow guide channel inlets and are discharged.
The second aspect, a flame guide cabin, include above-mentioned first aspect the water conservancy diversion passageway, flame guide cabin front end face and aircraft bottom end face are the same type, and the rear end face links to each other with the boost, and the wedge of water conservancy diversion passageway is located flame guide cabin's middle part, supports the smooth transition of surface and aircraft and boost about the flame guide cabin, and the inner flow way of water conservancy diversion passageway is located flame guide cabin's both sides, implements aircraft engine cold state air current and high-speed high temperature air current to derive.
In a third aspect, a method for designing a three-dimensional curved flow guide channel includes the following steps:
step (1), determining the sizes of an inlet and an outlet of a flow guide channel according to the sizes of an aircraft spray pipe and a booster;
determining the geometric configuration of the flow guide channel according to the inlet and the outlet of the flow guide channel, wherein the flow guide channel comprises a central wedge, two groups of side plates, a top plate and a bottom plate which are positioned on two sides of the wedge, the wedge is of a symmetrical V-shaped shell structure, the head part of the wedge is of a linear structure positioned at the inlet of the flow guide channel, the inlet of the flow guide channel is divided into two parts, and the two wings are opened to enable the tail part of the wedge to be of an arc structure and be connected with the booster; the two wing curved surfaces and the two groups of side plates, the top plate and the bottom plate respectively form two inner flow channels of a flow guide channel;
step (3), carrying out cold-state and hot-state flow refined numerical simulation on the inner channel of the flow guide channel, verifying whether the design scheme has shock wave/boundary layer interference and separation vortex, monitoring outlet flow, and determining whether the design index is met; if the design index requirements cannot be met, returning to the step (2) to re-determine the geometric configuration of the flow guide channel until the design index is met;
and (4) according to the requirements of the processing technology and the structural connection technology, adaptively modifying the scheme, carrying out cold-state and hot-state flow refined numerical simulation, meeting the requirements of the processing technology and the structural connection on the premise of meeting the design indexes in the step (3), and determining the final design scheme of the flow guide channel.
According to the design method of the three-dimensional curved surface flow guide channel, the flame guide cabin and the flow guide channel, provided by the invention, the following beneficial effects are achieved:
(1) according to the invention, through the three-dimensional outward convex type central cone diversion channel structure, in combination with a specific installation mode of the bottom plate and the top plate, the area ratio of the inlet to the outlet of the inner flow channel of the diversion channel, the wedge angle, the passivation radius of the wedge head, the length of the side plate, the included angle between the side plate and the incoming flow direction and the like, the shock wave generated by the incoming flow falling body in the diversion channel is effectively reduced, and the risk of flow blockage is increased;
(2) the wedge is integrally formed, so that the local structural strength is improved, the protruding size has certain redundancy, the process realizability is improved, and smooth flow guiding can be realized under certain processing errors;
(3) the invention realizes the design of a diversion channel with higher mass flow rate, the average mass flow rate of the outlet is improved by 9.5 percent, and the mass flow rate of the core area is improved by more than 30 percent;
(4) the three-dimensional curved surface flow guide channel provided by the invention can obviously reduce the flow loss of the inner flow channel, and the hypersonic speed resistance reduction of the aircraft is 10%.
Drawings
FIG. 1 is a schematic view of the configuration of an aircraft nozzle, a diversion channel and a booster according to a preferred embodiment of the present invention;
FIG. 2 is a schematic view showing the structure of a flow guide passage in a preferred embodiment of the present invention;
FIG. 3 is a schematic diagram illustrating a convex center wedge structure in a preferred embodiment of the present invention;
fig. 4 shows a schematic simulated flow cross section of the flow guide channel in example 1 near the top plate in a cold state (Y ═ 0 mm);
fig. 5 shows a schematic simulated flow cross section of the intermediate position (Y225 mm) of the flow guide channel in the cold state in example 1;
fig. 6 shows a schematic simulated flow cross section of the flow guide channel in example 1 near the bottom plate (Y450 mm) in a cold state;
fig. 7 shows a schematic simulated flow cross section of the flow guide channel in example 1, close to the top plate (Y ═ 0mm) in a hot state;
fig. 8 shows a schematic simulated flow cross section of the flow guide channel at the middle position (Y ═ 225mm) in the hot state in example 1;
fig. 9 shows a schematic simulated flow cross section of the flow guide channel in example 1, which is close to the bottom plate (Y-450 mm) in a thermal state.
Description of the reference numerals
1-a flow guide channel; 11-wedge; 12-side plates; 13-a top plate; 14-a base plate; 15-inner flow channel entrance; 16-an outlet; 2-a booster; and 3-spraying a pipe.
Detailed Description
The features and advantages of the present invention will become more apparent and appreciated from the following detailed description of the invention.
Aiming at the problems that a diversion channel is influenced by the combined action of internal and external flows, separation vortex is generated and blocking risk exists due to the fact that a shock wave boundary layer is prone to interfering flow in the channel, the inventor conducts a large amount of research, and provides a three-dimensional outward convex type central cone diversion channel structure on the basis of a two-dimensional plane channel.
The details are as follows.
According to a first aspect of the invention, a three-dimensional curved flow guide channel is provided, as shown in fig. 1, the flow guide channel 1 is a main functional structure of a flame guide cabin, an inlet of a front flow guide channel is connected with an outlet of an aircraft nozzle 3, and the shape of the flow guide channel is adjusted according to the shape of the outlet of the nozzle, and is preferably rectangular or nearly rectangular; the rear end is connected to the booster 2 and is preferably circular or near circular in shape.
As shown in fig. 2, the flow guide channel 1 of the invention comprises a central wedge 11, two groups of side plates 12, a top plate 13 and a bottom plate 14 which are positioned at two sides of the wedge 11, wherein the wedge 11 is of a symmetrical V-shaped shell structure, the head part of the wedge is of a linear structure positioned at the inlet of the flow guide channel, the inlet of the flow guide channel is divided into two parts, two wings are opened, and the tail part of the wedge is of an arc structure and is used for being connected with the booster 2; two inner flow channels of a flow guide channel are respectively enclosed by the two wings and the side plate 12, the top plate 13 and the bottom plate 14, the upper edges of the curved surfaces of the two wings are crossed with the top plate, the lower edges of the curved surfaces of the two wings are crossed with the bottom plate, and cold airflow and high-temperature gas enter the inner flow channels at the two sides through the separated flow guide channel inlets and are discharged.
In a preferred embodiment of the present invention, as shown in fig. 3, the wedge 11 is an outward convex central wedge, that is, two wings of the wedge are convex cambered structures, and a transition process from the head to the tail of the wedge is a linear structure to the convex cambered structure; thus, when the inner flow passage inlet 15 is rectangular or nearly rectangular, the inner flow passage transitions from the inlet to the outlet from a rectangle to a quadrilateral enclosed by three straight lines and one arc line. The inner runner inlets 15 are divided flow guide channel inlets, and each inner runner inlet 15 is provided with an independent inner runner outlet 16 due to the division of the central wedge. Compared with the traditional non-cambered surface structure form, the central wedge structure protrudes outwards to be beneficial to supersonic flow to accelerate spraying, the design can adjust the flow area of the outlet of the inner flow passage to reduce the flow area, and although the cross section area of the outlet of the inner flow passage is reduced, the mass flow rate can be greatly improved, and the flow loss is effectively reduced. On the premise of ensuring that the wedge 11 is in an outward convex type, the invention allows certain redundancy to the outward convex size, namely, certain machining error exists, and the flow capacity of the flow guide channel can be effectively improved, thereby being beneficial to the realization of the structure.
In a preferred embodiment of the present invention, the wedges 11 are integrally formed, so that the local structural strength is improved compared to the splicing formation commonly used in the prior art.
In a preferred embodiment of the invention, the straight wedge head is passivated and has a round-cornered structure.
In a preferred embodiment of the invention, the base plate 14 is parallel to the lower surface of the aircraft nozzle 3, i.e. parallel to the incoming flow direction, in order to reduce the interference of the coupling of the internal and external flows.
In a preferred embodiment of the invention, the top plate 13 is lifted upwards from the direction of the aircraft to the direction of the booster to form a micro-expansion, so that supersonic flow is accelerated to spray; preferably the angle of elevation is between 4 and 10.
The inventor finds that the area ratio of the inlet 15 to the outlet 16 of the inner flow channel (namely the area ratio of the inlet to the outlet of the flow guide channel), the included angle of the wedge head, the passivation radius of the wedge head, the length of the side plate, the included angle between the side plate and the incoming flow direction and other parameters determine whether the cold and hot airflow can not be separated and flow guide is smooth.
After a large number of researches, the area ratio of the inlet 15 to the outlet 16 of the inner flow channel is 1.00-1.20: 1, preferably 1.00 to 1.10: 1. the ratio of the inlet area to the outlet area of the inner runner avoids over-low outlet pressure caused by over-large outlet area and avoids flow blockage caused by over-small outlet area.
The included angle of the wedge head part is 20-45 degrees, preferably 30-45 degrees. The included angle of the wedge head part is too small, so that the size of the whole flow guide channel and even the size of the inner flow channel are too long, the reliability of the structure is reduced, and the quality of the structure is increased; too large a volume will cause shock waves from the incoming fluid, increasing the risk of flow blockage, and the above ranges combine structural stability and flow requirements.
The passivating radius of the wedge head is 4-6 mm. The importance of the passivation radius of the wedge head is mainly caused by the position of the wedge head, the passivation radius range not only controls the local high-temperature thermal environment, but also reduces the shock wave strength, and avoids the generation of shock wave boundary layer interference; if the passivation radius is too large, the shock wave is easy to fall off; if the passivation radius is too small, local high temperature heat will be generated at the tip.
The length of the side plate is measured by the length ratio of the side plate 12 to the wedge bus, and the length ratio of the side plate 12 to the wedge bus is 1: 4 ~ 6, the curb plate 12 is 10 ~ 20 with the direction contained angle that comes, and above-mentioned scope does benefit to and plays the effect that hinders the outflow and disturb the internal flow channel.
According to a second aspect of the present invention there is provided a flame guide chamber comprising a flow guide channel according to the first aspect above. The flame guide cabin is mainly used for connecting an aircraft and the booster 2 and guiding out incoming flow, the front end face of the flame guide cabin is in the same shape with the bottom end face of the aircraft, the shape of the flame guide cabin can be adjusted according to the shape adaptability of the bottom end face, such as a rectangle or a nearly rectangle, the rear end face of the flame guide cabin is connected with the booster 2, the shape of the flame guide cabin can be adjusted according to the shape adaptability of the head of the booster, such as a circle or a nearly circle, a wedge 11 of a flow guide channel is positioned in the middle of the flame guide cabin, the upper outer surface and the lower outer surface of the flame guide cabin are supported to be in smooth transition with the aircraft and the booster 2, and inner flow channels of the.
According to a third aspect of the present invention, there is provided a method for designing a three-dimensional curved flow guide channel, comprising the steps of:
(1) the sizes of the inlet and the outlet of the flow guide channel are determined according to the sizes of the jet pipe and the booster of the aircraft, so that the condition that the outlet pressure is too low due to too large outlet area and the condition that the flow is blocked due to too small outlet area are avoided;
(2) determining the geometric configuration of the flow guide channel according to the inlet and the outlet of the flow guide channel, wherein the flow guide channel 1 comprises a central wedge 11, two groups of side plates 12, a top plate 13 and a bottom plate 14 which are positioned at two sides of the wedge 11, the wedge 11 is of a symmetrical V-shaped shell structure, the head part of the wedge is of a linear structure positioned at the inlet of the flow guide channel, the inlet of the flow guide channel is divided into two parts, and the two wings are opened to enable the tail part of the wedge to be of an arc structure for connecting with the booster 2; the two wing curved surfaces and the two groups of side plates 12, the top plate 13 and the bottom plate 14 respectively form two inner flow channels of a flow guide channel;
(3) carrying out cold-state and hot-state flow refined numerical simulation on the inner channel of the flow guide channel, verifying whether the design scheme has shock wave/boundary layer interference and separation vortex, monitoring the outlet flow, and determining whether the design index is met; if the requirement of the design index cannot be met, namely shock wave/boundary layer interference or separation vortex occurs, returning to the step (2) to re-determine the geometric configuration of the flow guide channel until the design index is met;
(4) according to the processing technology and the structural connection requirement, the scheme is adaptively modified (such as passivation radius adjustment, material thickness adjustment and the like), cold-state and hot-state flow refined numerical simulation is carried out, the processing technology and the structural connection requirement are simultaneously met on the premise that the design index in the step 3 is met, and the final flow guide channel design scheme is determined. The processing technology requires that the processing is out of tolerance and the local passivation radius is too small due to the limitation of the processing precision of the curved surface. Structural attachment requires the presence of steps or seams, etc., as with aircraft or thrusters.
In the present invention, in step 2, parameters such as the shape of the wedge, the installation manner of the bottom plate and the top plate, the area ratio of the inlet to the outlet of the inner flow channel of the flow guide channel, the angle of the wedge, the passivation radius of the head of the wedge, the length of the side plate, and the included angle between the side plate and the incoming flow direction are consistent with the corresponding technical contents in the first aspect, and are not described herein again.
Examples
Example 1
FIG. 1 is a schematic view of a three-dimensional curved flow-guiding channel of the present invention, the front end of which is connected to the outlet of an aircraft nozzle 3 and is approximately rectangular in shape; the rear end is connected with the booster 2 and is in a shape of phi 1m circle.
Fig. 2 shows a schematic configuration diagram of a flow guide channel of the invention, which includes an outward convex central wedge 11, and two groups of top plates 13, bottom plates 14 and side plates 12 located at two sides of the wedge 11, wherein two curved surfaces at two sides of the wedge 11 respectively enclose two inner flow channels of the flow guide channel with the two groups of side plates 12, the top plates 13 and the bottom plates 14. The inlet of the flow guide channel is rectangular and vertical to the incoming flow direction, and the airflow in the spray pipe is divided into two parts by the wedge 11 of the flow guide channel and is discharged from the inner flow channels on the left side and the right side respectively. The wedge 11 is transited from a straight line to an outward arc surface from the inlet to the bottom end surface, the inlet of the inner channel is rectangular, and the outlet is a quadrangle with three straight lines and one arc line. The inner runner inlet/outlet area ratio is 1.05: 1, bottom plate 14 is parallel with the direction of incoming flow, and roof 13 is 5 contained angles with the square 5 contained angles that are of incoming flow, and curb plate 12 is 17.064 contained angles with the direction of incoming flow, and curb plate 12 minimum thickness 36mm, length are 298mm, play and hinder the effect that the outflow disturbed internal passage.
Fig. 3 shows a configuration of a flow guide channel wedge 11, the passivation radius of the wedge head is 5mm, the included angle between the wedge generatrix and the incoming flow is 21.167 degrees, the maximum inlet height is 490mm, and the maximum outlet height is 537 mm.
And performing integrated simulation evaluation on the internal and external flows of the whole aircraft on the designed flow guide channel, wherein the simulation state comprises cold-state working condition and hot-state working condition flow field simulation, the Ma range is 3-7, and the deviation ranges of the attack angle and the sideslip angle are +/-2 degrees. Fig. 4 to 9 are schematic diagrams showing the flow cross section of the diversion channel in cold and hot state flow numerical simulation of the present invention, fig. 4 to 6 respectively show the flow cross sections near the top plate, the middle position and the bottom plate in the cold state, fig. 7 to 9 respectively show the flow cross sections near the top plate, the middle position and the bottom plate in the hot state, and it can be determined from the streamline and pressure distribution that the inner flow channel flows uniformly, has no shock wave/boundary layer interference and no separation vortex, and can be smoothly guided out; the outlet flow rates of Ma6 near the top plate, the middle position and the bottom plate in the cold state are respectively 25.9kg/(s × m)2)、50kg/(s*m2)、25.7kg/(s*m2) (ii) a The outlet flow rates of the hot-state near the top plate, the middle position and the bottom plate are respectively 31kg/(s m)2)、37kg/(s*m2)、30kg/(s*m2) The design requirements of smooth cold and hot diversion of the diversion channel are met, and meanwhile, the mass flow rate of the core area of the channel is obviously increased due to the outward protrusion of the wedges, so that the through-flow capacity of the whole diversion channel is improved.
The flow guide channel is designed, and the average mass flow rate of the outlet is 30.8kg/(s m)2) Compared with a non-convex diversion channel, the average mass flow rate is improved by about 9.5 percent, and the mass flow rate of the flow core area is improved by more than 30 percent; the hypersonic resistance coefficient of the aircraft is 0.24, and compared with the non-convex diversion channel, the drag reduction is about 10%.
The invention has been described in detail with reference to specific embodiments and illustrative examples, but the description is not intended to be construed in a limiting sense. Those skilled in the art will appreciate that various equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its embodiments without departing from the spirit and scope of the present invention, which fall within the scope of the present invention. The scope of the invention is defined by the appended claims.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (10)
1. A three-dimensional curved surface flow guide channel is characterized in that an inlet of the flow guide channel at the front end of the flow guide channel is connected with an outlet of an aircraft spray pipe, and the rear end of the flow guide channel is connected with a booster;
the flow guide channel comprises a central wedge, two groups of side plates, a top plate and a bottom plate, wherein the two groups of side plates, the top plate and the bottom plate are positioned on two sides of the wedge, the wedge is of a symmetrical V-shaped shell structure, the head part of the wedge is of a linear structure positioned at the inlet of the flow guide channel and divides the inlet of the flow guide channel into two parts, two wings of the wedge are of an outward convex cambered surface structure, the two wings are opened, the tail part of the wedge is of an arc structure and the wedge; two inner flow channels of the flow guide channel are respectively enclosed by the two wings and the side plate, the top plate and the bottom plate, and cold airflow and high-temperature gas enter the inner flow channels at the two sides through the divided flow guide channel inlets and are discharged.
2. The three-dimensional curved flow guide channel according to claim 1, wherein the wedge head is passivated and has a rounded structure.
3. The three-dimensional curved flow guide channel according to claim 2, wherein the passivating radius of the wedge head is 4-6 mm.
4. The three-dimensionally curved flow-directing channel of claim 1, wherein the floor is parallel to a lower surface of the aircraft nozzle.
5. The three-dimensional curved flow guide channel of claim 1, wherein the top plate is lifted upwards from the direction of the aircraft to the direction of the booster to form a slight expansion, and the preferred lifting angle is 4-10 degrees.
6. The three-dimensional curved flow guide channel according to claim 1, wherein the area ratio of the inlet to the outlet of the inner flow channel is 1.00-1.20: 1.
7. the three-dimensional curved flow-guiding channel of claim 1, wherein the wedge angle is 20 ° to 45 °.
8. The three-dimensional curved flow guide channel according to claim 1, wherein the length ratio of the side plate to the wedge generatrix is 1: 4 ~ 6, the curb plate is 10 ~ 20 with the direction contained angle that comes.
9. A flame guiding cabin, characterized in that, including the diversion channel of any one of the above claims 1 to 8, the front end surface of the flame guiding cabin is in the same shape with the bottom end surface of an aircraft, the rear end surface is connected with a booster, the wedge of the diversion channel is positioned in the middle of the flame guiding cabin, the upper and lower outer surfaces of the flame guiding cabin are supported to be in smooth transition with the aircraft and the booster, and the inner flow channel of the diversion channel is positioned at two sides of the flame guiding cabin, so as to realize the export of the cold airflow and the high-speed and high-temperature airflow of the aircraft engine.
10. A design method of a three-dimensional curved surface flow guide channel is characterized by comprising the following steps:
step (1), determining the sizes of an inlet and an outlet of a flow guide channel according to the sizes of an aircraft spray pipe and a booster;
determining the geometric configuration of the flow guide channel according to the inlet and the outlet of the flow guide channel, wherein the flow guide channel comprises a central wedge, two groups of side plates, a top plate and a bottom plate which are positioned on two sides of the wedge, the wedge is of a symmetrical V-shaped shell structure, the head part of the wedge is of a linear structure positioned at the inlet of the flow guide channel, the inlet of the flow guide channel is divided into two parts, and the two wings are opened to enable the tail part of the wedge to be of an arc structure and be connected with the booster; the two wing curved surfaces and the two groups of side plates, the top plate and the bottom plate respectively form two inner flow channels of a flow guide channel;
step (3), carrying out cold-state and hot-state flow refined numerical simulation on the inner channel of the flow guide channel, verifying whether the design scheme has shock wave/boundary layer interference and separation vortex, monitoring outlet flow, and determining whether the design index is met; if the design index requirements cannot be met, returning to the step (2) to re-determine the geometric configuration of the flow guide channel until the design index is met;
and (4) according to the processing technology and the structural connection requirement, adaptively modifying the scheme, carrying out cold-state and hot-state flow refined numerical simulation, meeting the processing technology and the structural connection requirement on the premise of meeting the design index in the step (3), and determining the final design scheme of the flow guide channel.
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| CN202011148714.9A CN112307558B (en) | 2020-10-23 | 2020-10-23 | Three-dimensional curved surface flow guide channel, flame guide cabin and design method of flow guide channel |
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