CN112307558B - 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
- Publication number
- CN112307558B CN112307558B CN202011148714.9A CN202011148714A CN112307558B CN 112307558 B CN112307558 B CN 112307558B CN 202011148714 A CN202011148714 A CN 202011148714A CN 112307558 B CN112307558 B CN 112307558B
- Authority
- CN
- China
- Prior art keywords
- flow
- wedge
- channel
- diversion channel
- guide channel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000013461 design Methods 0.000 title claims abstract description 31
- 238000000034 method Methods 0.000 title claims abstract description 15
- 239000007921 spray Substances 0.000 claims abstract description 9
- 239000002737 fuel gas Substances 0.000 claims abstract description 6
- 230000035939 shock Effects 0.000 claims description 12
- 238000002161 passivation Methods 0.000 claims description 11
- 238000000926 separation method Methods 0.000 claims description 10
- 238000004088 simulation Methods 0.000 claims description 9
- 238000012545 processing Methods 0.000 claims description 8
- 238000005516 engineering process Methods 0.000 claims description 6
- 230000007704 transition Effects 0.000 claims description 5
- 238000012544 monitoring process Methods 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 4
- 238000011160 research Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000003044 adaptive effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/08—Fluids
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Geometry (AREA)
- Mathematical Optimization (AREA)
- General Engineering & Computer Science (AREA)
- Mathematical Analysis (AREA)
- Evolutionary Computation (AREA)
- Pure & Applied Mathematics (AREA)
- Computer Hardware Design (AREA)
- Aviation & Aerospace Engineering (AREA)
- Computational Mathematics (AREA)
- Automation & Control Theory (AREA)
- Algebra (AREA)
- Computing Systems (AREA)
- Fluid Mechanics (AREA)
- Mathematical Physics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
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 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 an booster; the guide channel comprises a central wedge and two groups of side plates, a top plate and a bottom plate which are positioned at two sides of the wedge, the wedge is of a symmetrical V-shaped shell structure, the head of the wedge is of a linear structure positioned at the inlet of the guide channel, the inlet of the guide channel is divided into two parts, two wings of the wedge are of an outwards convex cambered surface structure, the two wings are opened, and the tail of the wedge is of an arc structure and is used for being connected with the booster; the two wings, the side plate, the top plate and the bottom plate respectively form two inner flow passages of the diversion channel, and cold air flow and high-temperature fuel gas enter the inner flow passages at the two sides through the inlets of the diversion channel after being separated and are discharged. The three-dimensional convex type central cone diversion channel structure can smoothly guide out cold air flow and high-temperature fuel gas of the spray pipe of the aircraft, remarkably improves the mass flow rate and flow, and reduces the resistance of the aircraft.
Description
Technical Field
The invention belongs to the technical field of flow guide channel design, and particularly relates to a three-dimensional curved flow guide channel, a flame guide cabin and a flow guide channel design method.
Background
In order to prevent structural damage caused by low-frequency pulsation of an air inlet channel of an air vehicle, an air inlet channel protecting cover or a diversion interstage section is generally adopted for the air-breathing hypersonic air vehicle with an booster. If the power performance of the air suction type engine is considered to be verified in the boosting section, only a diversion interstage section design can be adopted, so that the whole aircraft is in an inner runner through-flow state, and once a diversion channel cannot conduct normal diversion under a cold state condition, the inner runner is blocked, incoming flow air intake is influenced, and the engine cannot be started; after the engine is ignited (in a hot state), the jet flow of the engine needs to be smoothly guided by the guide channel, and once the jet flow cannot be guided out of the inner flow channel to cause blockage, the work of the engine is affected.
The diversion channel is of a special structure and is influenced by the combined action of internal and external flows, the phenomenon that the shock boundary layer existing in the flow channel interferes with the flow is complex, separation vortex is easy to generate, and the risk of blockage exists, so that the diversion channel and the flow capacity thereof are required to be designed in a detailed optimization mode.
Disclosure of Invention
In order to overcome the defects in the prior art, the inventor performs intensive research and provides a three-dimensional curved surface flow guide channel and a design method thereof, so that the flow guide channel meets cold and hot flow guide requirements, namely cold air flow and high-temperature fuel gas of an aircraft spray pipe are smoothly led out, and meanwhile, requirements of separation, thermal environment, structure and the like of an aircraft and a booster are met, thereby completing the invention.
The technical scheme provided by the invention is as follows:
in the first aspect, a three-dimensional curved surface diversion channel is provided, wherein a diversion channel inlet at the front end of the diversion channel is connected with an outlet of an aircraft spray pipe, and the rear end of the diversion channel is connected with an booster;
the guide channel comprises a central wedge and two groups of side plates, a top plate and a bottom plate which are positioned at two sides of the wedge, the wedge is of a symmetrical V-shaped shell structure, the head of the wedge is of a linear structure positioned at the inlet of the guide channel, the inlet of the guide channel is divided into two parts, two wings of the wedge are of an outwards convex cambered surface structure, the two wings are opened, and the tail of the wedge is of an arc structure and is used for being connected with the booster; the two wings, the side plate, the top plate and the bottom plate respectively form two inner flow passages of the diversion channel, and cold air flow and high-temperature fuel gas enter the inner flow passages at the two sides through the inlets of the diversion channel after being separated and are discharged.
In a second aspect, a flame guiding cabin includes the guide channel of the first aspect, the front end surface of the flame guiding cabin is in the same shape as the bottom end surface of the aircraft, the rear end surface of the flame guiding cabin is connected with the booster, the wedge of the guide 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, the inner flow channels of the guide channel are positioned on two sides of the flame guiding cabin, and cold air flow and high-speed high-temperature air flow of the engine of the aircraft are guided out.
In a third aspect, a method for designing a three-dimensional curved surface diversion channel includes the following steps:
step (1), determining the inlet and outlet sizes of a diversion channel according to the sizes of an aircraft spray pipe and a booster;
step (2), determining the geometric configuration of the diversion channel according to the inlet and the outlet of the diversion channel, wherein the diversion channel comprises a central wedge and two groups of side plates, a top plate and a bottom plate which are positioned at two sides of the wedge, the wedge is of a symmetrical V-shaped shell structure, the head part is of a linear structure positioned at the inlet of the diversion channel, the inlet of the diversion channel is divided into two parts, and the two wings are opened to enable the tail part to be of an arc structure for being connected with the booster; the curved surfaces of the two wings respectively enclose two inner flow passages of the diversion channel with the two groups of side plates, the top plate and the bottom plate;
step (3), carrying out cold state and hot state flow refinement numerical simulation on the inner channel of the diversion channel, verifying whether shock wave/boundary layer interference exists in the design scheme, whether separation vortex exists or not, monitoring the outlet flow, and determining whether the design index is met or not; if the design index requirements cannot be met, returning to the step (2) to redetermine the geometric configuration of the diversion channel until the design index is met;
and (4) adaptively modifying the scheme according to the requirements of a processing tool and a structural connection process, carrying out cold state and hot state flow refinement numerical simulation, and determining a final diversion channel design scheme while meeting the requirements of the processing process and the structural connection on the premise of meeting the design indexes of the step (3).
According to the design method of the three-dimensional curved surface flow guide channel, the flame guide cabin and the flow guide channel, the design method has the following beneficial effects:
(1) According to the invention, by combining the three-dimensional convex central cone diversion channel configuration with the 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, shock waves generated by incoming flow falling in the diversion channel are 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 convex size has certain redundancy, the process realizability is improved, and smooth flow guide can be realized under certain machining errors;
(3) The invention realizes the design of a diversion channel with higher mass flow rate, the average mass flow rate of an outlet is improved by 9.5%, and the mass flow rate of a core area is improved by more than 30%;
(4) According to the three-dimensional curved surface diversion channel, the flow loss of the inner flow channel is obviously reduced, and the hypersonic speed of an aircraft is reduced by 10%.
Drawings
FIG. 1 shows 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 diversion channel in a preferred embodiment of the present invention;
FIG. 3 is a schematic view showing the structure of a male center wedge in a preferred embodiment of the present invention;
fig. 4 shows a schematic diagram of a simulated flow cross section of the diversion channel of example 1 in the cold state near the top plate (y=0 mm);
fig. 5 shows a schematic diagram of a simulated flow cross section of the diversion channel of example 1 at an intermediate position (y=225 mm) in the cold state;
fig. 6 shows a schematic diagram of a simulated flow cross section of the diversion channel in example 1 in the cold state near the bottom plate (y=450 mm);
fig. 7 shows a schematic diagram of a simulated flow cross section near the top plate (y=0 mm) in the hot state of the diversion channel in example 1;
fig. 8 shows a schematic diagram of a simulated flow cross section of the hot intermediate position (y=225 mm) of the diversion channel in example 1;
fig. 9 shows a schematic diagram of a simulated flow cross section of the flow guide channel of example 1 in a thermal state close to the bottom plate (y=450 mm).
Description of the reference numerals
1-a diversion channel; 11-wedge; 12-side plates; 13-top plate; 14-a bottom plate; 15-an inner flowpath inlet; 16-outlet; 2-a booster; 3-spray pipe.
Detailed Description
The features and advantages of the present invention will become more apparent and clear from the following detailed description of the invention.
Aiming at the problems that the flow guide channel is influenced by the combined action of internal and external flows, and a shock wave boundary layer is easy to interfere with the flow in the flow channel to cause separation vortex and blockage risk, the inventor performs a great deal of research, and provides a three-dimensional convex type central cone flow guide channel configuration on the basis of a two-dimensional plane flow channel, and the combination of specific structures can obviously improve the mass flow rate and flow and reduce the resistance of an aircraft.
The details are as follows.
According to a first aspect of the present invention, there is provided a three-dimensional curved surface flow guide channel, as shown in fig. 1, wherein the flow guide channel 1 is a main functional structure of a flame guide cabin, an inlet of the flow guide channel at the front end is connected with an outlet of a jet pipe 3 of an aircraft, and the shape is adjusted according to the shape of the outlet of the jet pipe, and is preferably rectangular or nearly rectangular; the rear end is connected to the booster 2, preferably in the shape of a circle or near circle.
As shown in fig. 2, the flow guiding channel 1 in the present invention includes a central wedge 11 and two sets of side plates 12, top plates 13 and bottom plates 14 located at two sides of the wedge 11, wherein the wedge 11 is a symmetrical V-shaped shell structure, the head is a linear structure located at the inlet of the flow guiding channel, the inlet of the flow guiding channel is divided into two parts, the two wings are opened and the tail is in a circular arc structure for connecting with the booster 2; the two wings respectively encircle two inner flow channels of the diversion channel with 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 intersecting lines with the top plate, the lower edges of the curved surfaces of the two wings are intersecting lines with the bottom plate, and cold air flow and high-temperature fuel gas are discharged after entering the inner flow channels on the two sides through the separated inlets of the diversion channel.
In a preferred embodiment of the present invention, as shown in fig. 3, the wedge 11 is a convex center wedge, that is, two wings of the wedge are in a convex arc structure, and a transition process from the head to the tail of the wedge is a straight structure to the convex arc structure; thus, when the inner flow path inlet 15 is rectangular or nearly rectangular, the inner flow path transitions from the inlet to the outlet from rectangular to a quadrilateral defined by a trilateral straight line and a one-sided arc. The inner flow channel inlets 15 are divided flow guide channel inlets, and each inner flow channel inlet 15 is provided with an independent inner flow channel outlet 16 due to the separation of the central wedges. Compared with the traditional non-cambered surface structural form, the central wedge structure is convex to be favorable for accelerating the ultrasonic flow and spraying, and the design can adjust the flow area of the outlet of the inner flow channel to be reduced, and the mass flow rate can be greatly improved while the cross-sectional area of the outlet of the inner flow channel is reduced, so that the flow loss is effectively reduced. On the premise of ensuring that the wedge 11 is convex, the invention allows certain redundancy to the outer convex size, namely certain machining errors exist, can still effectively improve the flow capacity of the flow guide channel, and is beneficial to structural realization.
In a preferred embodiment of the present invention, the wedge 11 is integrally formed, which improves the local structural strength compared to the splice forming commonly used in the prior art.
In a preferred embodiment of the invention, the straight wedge head is passivated to form a rounded corner structure.
In a preferred embodiment of the invention, the floor 14 is parallel to the lower surface of the aircraft nozzle 3, i.e. parallel to the direction of the incoming flow, in order to reduce the internal and external flow coupling disturbances.
In a preferred embodiment of the present invention, the top plate 13 is lifted upwards from the direction of the aircraft to the direction of the booster to form micro-expansion, which is beneficial to the acceleration and ejection of supersonic flow; the preferred lifting angle is 4-10 deg..
The present inventors have found through research that the area ratio of the inlet 15 to the outlet 16 of the inner flow channel (i.e. the area ratio of the inlet to the outlet of the flow guiding 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, etc. determine whether the cold and hot air flows can be smoothly guided without separation.
After a lot 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 flow passage avoids the excessively low outlet pressure caused by excessively large outlet area on one hand and the flow blockage caused by excessively small outlet area on the other hand.
The included angle of the wedge head is 20-45 degrees, preferably 30-45 degrees. Too small included angle of the wedge head can cause overlong size of the whole diversion channel and even the inner diversion channel, the structural reliability is reduced, and the structural quality is increased; too large a flow will cause shock waves to come off the body, increasing the risk of flow blockage, while the above ranges combine structural stability and flowability requirements.
The passivation 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, and the passivation radius range controls the local high-temperature environment and reduces the shock intensity, so that the interference of a shock boundary layer is avoided; if the passivation radius is too large, the shock wave is easy to be separated; if the passivating radius is too small, localized high temperature may be generated at the wedge head.
The length of the side plate is measured by the length ratio of the side plate 12 to the length of the wedge bus, and the length ratio of the side plate 12 to the length of the wedge bus is 1: 4-6, the included angle between the side plate 12 and the incoming flow direction is 10-20 degrees, and the range is favorable for preventing the interference of the outflow flow to the inner flow path.
According to a second aspect of the present invention, there is provided a flame guide comprising the flow guide channel of the first aspect. The flame guide cabin is mainly used for connecting an aircraft with the booster 2 and guiding incoming flows, the front end face of the flame guide cabin is in the same shape as the bottom end face of the aircraft, the shape of the flame guide cabin is adaptively adjusted according to the shape of the bottom end face, for example, the flame guide cabin can be rectangular or nearly rectangular, the rear end face of the flame guide cabin is connected with the booster 2, the shape of the flame guide cabin is adaptively adjusted according to the shape of the head of the booster, for example, the flame guide cabin can be round or nearly round, 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 smoothly transition with the aircraft and the booster 2, and inner flow channels of the flow guide channels are positioned on two sides of the flame guide cabin, so that cold air flow and high-speed high-temperature air flow of an aircraft engine are guided out.
According to a third aspect of the present invention, there is provided a method for designing a three-dimensional curved surface flow guide channel, comprising the steps of:
(1) The sizes of the inlet and the outlet of the diversion channel are determined according to the sizes of the jet pipe and the booster of the aircraft, so that the situation that the outlet pressure is too low due to the overlarge area of the outlet is avoided, and the situation that the flow is blocked due to the overlarge area of the outlet is also avoided;
(2) The geometric configuration of the diversion channel is determined according to the inlet and the outlet of the diversion channel, wherein the diversion 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 is of a linear structure positioned at the inlet of the diversion channel, the inlet of the diversion channel is divided into two parts, and two wings are opened to enable the tail part to be of an arc structure for being connected with the booster 2; the curved surfaces of the two wings respectively enclose two inner flow passages of the diversion channel with the two groups of side plates 12, the top plate 13 and the bottom plate 14;
(3) Carrying out cold state and hot state flow refined numerical simulation on the inner channel of the diversion channel, verifying whether shock wave/boundary layer interference exists in the design scheme, whether separation vortex exists or not, monitoring the outlet flow, and determining whether the design index is met or not; if the design index requirement cannot be met, namely shock wave/boundary layer interference or separation vortex occurs, returning to the step (2) to redetermine the geometric configuration of the diversion channel until the design index is met;
(4) And (3) carrying out adaptive modification (such as passivation radius adjustment, material thickness adjustment and the like) on the scheme according to the processing technology and the structure connection requirement, carrying out cold state and hot state flow refinement numerical simulation, and determining the final diversion channel design scheme on the premise of meeting the processing technology and the structure connection requirement on the premise of meeting the design index of the step (3). The processing technology requirements such as the limit of the processing precision of the curved surface are out of tolerance, and the local passivation radius is too small to be realized. Structural connection requirements such as the presence of steps or joints when connecting with an aircraft or booster, etc.
In the step 2, the shape of the wedge, the 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 flow guide 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 other parameters are consistent with the corresponding technical content in the first aspect, and are not repeated herein.
Examples
Example 1
FIG. 1 shows a schematic view of a three-dimensional curved surface flow channel of the present invention, the front end of which is connected to the outlet of an aircraft nozzle 3, which is approximately rectangular in shape; the rear end is connected with the booster 2 and is round with the shape of phi 1 m.
Fig. 2 shows a schematic view of a diversion channel configuration of the present invention, which includes an outer convex central wedge 11, two groups of top plates 13, bottom plates 14 and side plates 12 located at two sides of the wedge 11, and two inner flow paths of the diversion channel are respectively surrounded by curved surfaces at two sides of the wedge 11 and the two groups of side plates 12, top plates 13 and bottom plates 14. The inlet of the diversion channel is rectangular and is perpendicular to the incoming flow direction, and the airflow in the spray pipe is divided into two parts by the wedge 11 of the diversion channel and is discharged from the inner flow channels on the left side and the right side respectively. The wedge 11 is changed from a straight line into an outer arc surface from an inlet to a bottom end surface, the inlet of the inner channel is rectangular, and the outlet is changed into a quadrangle with a trilateral straight line and a one-sided arc line. The inlet/outlet area ratio of the inner runner is 1.05:1, the bottom plate 14 is parallel with the incoming flow direction, the roof 13 is 5 degrees contained angles with the incoming flow direction, the curb plate 12 is 17.064 degrees contained angles with the incoming flow direction, the minimum thickness of curb plate 12 36mm, length is 298mm, plays the effect that prevents outflow to the internal channel interference.
Fig. 3 shows the configuration of the guide channel wedge 11, the passivation radius of the wedge head is 5mm, the wedge generatrix forms an included angle of 21.167 degrees with the incoming flow, the maximum height of the inlet is 490mm, and the maximum height of the outlet is 537mm.
And carrying out integrated simulation evaluation on the internal and external flows of the full-aircraft on the designed diversion 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 attack angle and sideslip angle pulling deviation range is +/-2 degrees. As shown in fig. 4-9, the flow sections of the diversion channel near the top plate, the middle position and the bottom plate in the cold state are shown in fig. 4-6, and the flow sections near the top plate, the middle position and the bottom plate in the hot state are shown in fig. 7-9, so that the flow uniformity of the inner flow channel can be judged from the streamline and the pressure distribution, the shock wave/boundary layer interference and the separation vortex can be avoided, and the flow can be smoothly led out; the outlet flow rates near the top plate, the middle position and the bottom plate in the cold state of Ma6 are 25.9 kg/(s.multidot.m) 2 )、50kg/(s*m 2 )、25.7kg/(s*m 2 ) The method comprises the steps of carrying out a first treatment on the surface of the The outlet flow rates near the top plate, the middle position and the bottom plate in the thermal state are respectively 31 kg/(s.times.m) 2 )、37kg/(s*m 2 )、30kg/(s*m 2 ) The design requirements of smooth diversion of the diversion channel in a cold state and a hot state are met, meanwhile, the mass flow rate of the core area of the channel is obviously increased due to the fact that the wedges are protruded, and the flow capacity of the whole diversion channel is improved.
The design of the diversion channel in the invention has the average mass flow rate of 30.8 kg/(s.times.m) 2 ) Compared with a non-convex flow guide channel, the average mass flow rate is improved by about 9.5%, and the mass flow rate of a flow core area is improved by more than 30%; the hypersonic drag coefficient of the aircraft is 0.24, which is about 10% compared with the drag reduction of a non-convex diversion channel.
The invention has been described in detail in connection with the specific embodiments and exemplary examples thereof, but such description is not to be construed as limiting the invention. It will be understood by those skilled in the art 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, and these fall within the scope of the present invention. The scope of the invention is defined by the appended claims.
What is not described in detail in the present specification is a well known technology to those skilled in the art.
Claims (5)
1. The three-dimensional curved surface diversion channel is characterized in that a diversion channel inlet at the front end of the diversion channel is connected with an outlet of an aircraft spray pipe, and the rear end of the diversion channel is connected with an booster;
the guide channel comprises a central wedge and two groups of side plates, a top plate and a bottom plate which are positioned at two sides of the wedge, the wedge is of a symmetrical V-shaped shell structure, the head of the wedge is of a linear structure positioned at the inlet of the guide channel, the inlet of the guide channel is divided into two parts, two wings of the wedge are of an outwards convex cambered surface structure, the two wings are opened, and the tail of the wedge is of an arc structure and is used for being connected with the booster; two wings, a side plate, a top plate and a bottom plate respectively form two inner flow channels of the diversion channel, and cold air flow and high-temperature fuel gas enter the inner flow channels at two sides through the inlets of the diversion channel after being separated and are discharged;
the wedge head is passivated to be a rounded corner structure, and the passivation radius is 4-6mm;
the wedge angle is 20-45 degrees;
the length ratio of the side plate to the wedge bus is 1: 4-6, wherein the included angle between the side plate and the incoming flow direction is 10-20 degrees;
the area ratio of the inlet to the outlet of the inner runner is 1.00-1.20:1.
2. the three-dimensional curved flow-directing channel of claim 1, wherein the floor is parallel to a lower surface of the aircraft nozzle.
3. The three-dimensional curved surface diversion tunnel of claim 1, wherein the roof is raised 4 ° to 10 ° upward from the aircraft direction to the booster direction.
4. A flame guide cabin characterized by comprising the flow guide channel as claimed in any one of claims 1 to 3, wherein the front end surface of the flame guide cabin is co-molded with the bottom end surface of an aircraft, the rear end surface of the flame guide cabin is connected with a booster, a wedge of the flow guide channel is positioned in the middle of the flame guide cabin and is used for supporting the upper and lower outer surfaces of the flame guide cabin to smoothly transition with the aircraft and the booster, and inner flow channels of the flow guide channel are positioned on two sides of the flame guide cabin and are used for guiding cold air flow and high-speed high-temperature air flow of an engine of the aircraft.
5. A method of designing a three-dimensional curved surface flow guide channel as defined in claim 1, comprising the steps of:
step (1), determining the inlet and outlet sizes of a diversion channel according to the sizes of an aircraft spray pipe and a booster;
step (2), determining the geometric configuration of the diversion channel according to the inlet and the outlet of the diversion channel, wherein the diversion channel comprises a central wedge and two groups of side plates, a top plate and a bottom plate which are positioned at two sides of the wedge, the wedge is of a symmetrical V-shaped shell structure, the head part is of a linear structure positioned at the inlet of the diversion channel, the inlet of the diversion channel is divided into two parts, and the two wings are opened to enable the tail part to be of an arc structure for being connected with the booster; the curved surfaces of the two wings respectively enclose two inner flow passages of the diversion channel with the two groups of side plates, the top plate and the bottom plate;
step (3), carrying out cold state and hot state flow refinement numerical simulation on the inner channel of the diversion channel, verifying whether shock wave/boundary layer interference exists in the design scheme, whether separation vortex exists or not, monitoring the outlet flow, and determining whether the design index is met or not; if the design index requirements cannot be met, returning to the step (2) to redetermine the geometric configuration of the diversion channel until the design index is met;
and (4) adaptively modifying the scheme according to the processing technology and the structure connection requirement, carrying out cold state and hot state flow refinement numerical simulation, and determining a final diversion channel design scheme while meeting the processing technology and the structure connection requirement on the premise of meeting the design index of the step (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112307558A CN112307558A (en) | 2021-02-02 |
| CN112307558B true CN112307558B (en) | 2024-02-09 |
Family
ID=74327516
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011148714.9A Active 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 |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112307558B (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109840378A (en) * | 2019-01-31 | 2019-06-04 | 北京航天发射技术研究所 | Complicated launching condition rocket dynamic is taken off gas flow field grid model generation method |
| CN210568405U (en) * | 2019-08-16 | 2020-05-19 | 天津津滨石化设备有限公司 | Full-premixing condensing low-nitrogen cast silicon-aluminum gas boiler |
| CN111767613A (en) * | 2020-07-10 | 2020-10-13 | 南京航空航天大学 | Design method of fixed-geometry high-speed air inlet channel inlet section with offset compression surface |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7568347B2 (en) * | 2005-07-22 | 2009-08-04 | Lockheed Martin Corporation | Method for designing flowfield molded hypersonic inlet for integrated turbojet and ram-scramjet applications |
| US20180285497A1 (en) * | 2017-03-31 | 2018-10-04 | The Government Of The United States Of America, As Represented By The Secretary Of The Navy | Numerical Modeling and Performance Analysis of a Scramjet Engine with a Controllable Waverider Inlet Design |
-
2020
- 2020-10-23 CN CN202011148714.9A patent/CN112307558B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109840378A (en) * | 2019-01-31 | 2019-06-04 | 北京航天发射技术研究所 | Complicated launching condition rocket dynamic is taken off gas flow field grid model generation method |
| CN210568405U (en) * | 2019-08-16 | 2020-05-19 | 天津津滨石化设备有限公司 | Full-premixing condensing low-nitrogen cast silicon-aluminum gas boiler |
| CN111767613A (en) * | 2020-07-10 | 2020-10-13 | 南京航空航天大学 | Design method of fixed-geometry high-speed air inlet channel inlet section with offset compression surface |
Non-Patent Citations (2)
| Title |
|---|
| 大型火箭发射时发动机噪声预示方法研究;张维纲;强度与环境(第5期);第11-17页 * |
| 岳连捷 等.三面压缩进气道三维激波相干研究.中国力学学会学术大会'2009论文摘要集.2009,第1-8页. * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112307558A (en) | 2021-02-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| WO2022095163A1 (en) | Internal-external flow decoupled dual-waverider high-speed airbreathing aircraft and generation method therefor | |
| JP4340769B2 (en) | Method and apparatus for reducing distortion loss in gas turbine engine airflow | |
| CN109723570B (en) | Throat offset pneumatic thrust vectoring nozzle with asymmetric aft-body profile | |
| US20120168117A1 (en) | Automotive HVAC Diffuser With Cooperating Wall Guide And Vane | |
| CN108590884B (en) | Vertical take-off and landing type throat offset pneumatic vectoring nozzle based on guide plate | |
| CN111767613B (en) | Design method for inlet section of fixed-geometry high-speed air inlet channel with offset compression surface | |
| CN208417090U (en) | Two-dimensional-configuration multi-support-plate ejector | |
| CN110671231B (en) | Throat offset type pneumatic thrust vectoring nozzle with front spoiler | |
| CN112307558B (en) | Three-dimensional curved surface flow guide channel, flame guide cabin and design method of flow guide channel | |
| US10851659B2 (en) | Vortex generating device | |
| EP2865874B1 (en) | Turbofan engine with passive thrust vectoring | |
| CN110173373B (en) | Double-flow-passage S-shaped spray pipe | |
| CN112963268B (en) | Throat offset pneumatic vectoring nozzle of small-hole jet flow | |
| CN113120244B (en) | Design method for improving performance of backpack parallel double-engine double-S-bend air inlet passage | |
| CN105781790A (en) | Segmented convergence type double-S-curve binary mixed exhaust system | |
| CN103612746B (en) | The wing hangs the dome structure of hanging in airplane | |
| US8959924B2 (en) | Aircraft turbofan engine | |
| CN113153446B (en) | Turbine guider and centripetal turbine with high expansion ratio | |
| CN112065604B (en) | Low-infrared characteristic spray pipe | |
| CN105464838A (en) | Methods and apparatus for passive thrust vectoring and plume deflection | |
| CN111706409B (en) | Corrugated air film hole with branch hole | |
| CN109723571B (en) | Throat offset type pneumatic thrust vectoring nozzle with trapezoidal section and aircraft equipped with same | |
| CN115571366B (en) | Design method of wave-type rotating wing of aerospace vehicle | |
| WO2020199370A1 (en) | Aero-engine turbine blade having cooling structure | |
| JP2002349201A (en) | Turbin rotor blade |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |