CN113202563A - Coaxial reverse two-stage turbine device for weakening energy of tail flame emitted by missile - Google Patents
Coaxial reverse two-stage turbine device for weakening energy of tail flame emitted by missile Download PDFInfo
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- CN113202563A CN113202563A CN202110434342.4A CN202110434342A CN113202563A CN 113202563 A CN113202563 A CN 113202563A CN 202110434342 A CN202110434342 A CN 202110434342A CN 113202563 A CN113202563 A CN 113202563A
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- turbine shaft
- stage turbine
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/30—Non-positive-displacement machines or engines, e.g. steam turbines characterised by having a single rotor operable in either direction of rotation, e.g. by reversing of blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a coaxial reverse two-stage turbine device for weakening the energy of missile launching tail flame, which guides the jet flow of the missile launching tail flame by a guide cone, changes the direction of the jet flow once, the jet flow guided by the guide cone acts on the first-stage turbine blades to drive the first-stage turbine to rotate, so that the secondary change of the direction of the jet flow is realized, the first-stage turbine is driven by the power transmission device after rotating to drive the second-stage turbine to rotate in the opposite direction, the second-stage turbine blades act to realize the tertiary change of the direction of the jet flow, the change of the direction of the jet flow every time can play the role of dispersing the energy of the jet flow and reducing the flow speed of the jet flow of the tail flame, meanwhile, the vector direction of partial tail flame jet flow is changed, the energy field of the tail flame jet flow is reduced, the quantity of stone impurities which can be rolled up by the tail flame jet flow is reduced, the initial kinetic energy of the impurities in the tail flame jet flow is weakened, and the damage to surrounding personnel and equipment is reduced or even avoided; the device has the advantages of simple structure, reasonable design, convenient use and the like.
Description
Technical Field
The invention relates to the technical field of missile accessories, in particular to a coaxial reverse two-stage turbine device for weakening the energy of a tail flame emitted by a missile.
Background
Missiles, as modern defense weapon systems, have been equipped more and more in various military classes. Various technical studies on missile technology are also on the rise. In the process from ignition to takeoff, the heat-emitting missile can jet out high-speed and high-temperature tail flame fuel gas, and the tail flame fuel gas can generate strong thermal shock on an emission platform.
When the missile is launched in the past, tail flame jet flow launched by the missile rapidly extends outwards to form a vortex, a large amount of impurities such as stones can be curled up, the impurities are scattered at a high speed in a launching field, surrounding personnel and equipment are easily damaged, and huge potential safety hazards exist.
Therefore, how to develop a device to reduce the damage caused by the missile launching tail flame is a problem to be solved urgently.
Disclosure of Invention
In view of the above, the invention provides a coaxial reverse rotation two-stage turbine device for weakening the energy of the missile launching tail flame, so that the energy of the missile launching tail flame is weakened, the quantity of impurities such as stones rolled up by the missile launching tail flame is reduced, and potential safety hazards are reduced.
The invention provides a technical scheme, in particular to a coaxial reverse two-stage turbine device for weakening the energy of tail flame emitted by a missile, which comprises: the device comprises a guide cone, a first-stage turbine, a second-stage turbine, a power transmission device and a fixing frame;
the first stage turbine includes: the turbine comprises a first-stage turbine shaft, a first-stage baffle and a plurality of first-stage turbine blades;
the diameter of the upper part of the primary turbine shaft is larger than that of the lower part of the primary turbine shaft, and a plurality of mounting grooves are arranged on the side wall of the upper part of the primary turbine shaft at intervals;
the first-stage turbine blades correspond to the mounting grooves in the side wall of the first-stage turbine shaft one by one, and each first-stage turbine blade is mounted in the corresponding mounting groove;
the primary baffle plate is sleeved outside the primary turbine shaft and is fixedly connected with the lower end face of the upper part of the primary turbine shaft;
the guide cone is positioned above the first-stage turbine, and the lower end of the guide cone is fixedly connected with the upper end of the first-stage turbine shaft;
the two-stage turbine includes: the turbine comprises a secondary turbine shaft, a secondary baffle and a plurality of secondary turbine blades;
the center of the secondary turbine shaft is provided with a through mounting hole, the secondary turbine shaft is sleeved outside the lower part of the primary turbine shaft through the mounting hole, the diameter of the upper part of the secondary turbine shaft is larger than that of the lower part of the secondary turbine shaft, and a plurality of mounting grooves are arranged on the side wall of the upper part of the secondary turbine shaft at intervals;
the secondary turbine blades correspond to the mounting grooves in the side wall of the secondary turbine shaft one by one, and each secondary turbine blade is mounted in the corresponding mounting groove;
the secondary baffle is sleeved outside the secondary turbine shaft and is fixedly connected with the lower end face of the upper part of the secondary turbine shaft;
the power transmission device is positioned below the secondary turbine, the power input end of the power transmission device is in driving connection with the primary turbine shaft, and the power output end of the power transmission device is in driving connection with the secondary turbine shaft;
the fixing frame is positioned below the power transmission device and is fixedly connected with the power transmission device.
Preferably, the power transmission device includes: the device comprises a shell, a bottom plate, a first large bevel gear, a second large bevel gear and a plurality of small bevel gears;
the lower end of the shell is open, and the upper end of the shell is provided with a mounting hole;
the bottom plate is plugged and installed at an opening at the lower end of the shell and forms a cavity with the shell in an enclosing manner;
the first large bevel gear is positioned in the cavity and fixedly sleeved outside the secondary turbine shaft;
the second large bevel gear is positioned in the cavity and arranged below the first large bevel gear, and the second large bevel gear is fixedly sleeved outside the primary turbine shaft;
the plurality of small bevel gears are located between the first large bevel gear and the second large bevel gear and are respectively meshed with the first large bevel gear and the second large bevel gear, and each small bevel gear is rotationally connected with the side wall of the shell.
Preferably, a limiting groove is formed in the center of the bottom plate, and the lower end of the primary turbine shaft is rotationally limited in the limiting groove.
Further preferably, the coaxial reverse rotation two-stage turbine device for attenuating the energy of the tail flame emitted by the missile further comprises: a plurality of first set screws;
countersunk holes which are in one-to-one correspondence with the first positioning screws are formed in the first-stage baffle plates at intervals along the circumferential direction;
through holes which correspond to the countersunk holes one to one are formed in the upper part of the first turbine shaft at intervals along the circumferential direction;
threaded blind holes which are in one-to-one correspondence with the through holes are formed in the lower end face of the flow guide cone at intervals along the circumferential direction;
and the first positioning screw penetrates through the counter bore on the first-stage baffle plate and the through hole on the first turbine shaft in sequence, is installed in the threaded blind hole on the guide cone in a threaded manner, and fixedly connects the first-stage baffle plate, the first turbine shaft and the guide cone.
Further preferably, the coaxial reverse rotation two-stage turbine device for attenuating the energy of the tail flame emitted by the missile further comprises: a plurality of second set screws;
countersunk holes which are in one-to-one correspondence with the second positioning screws are formed in the secondary baffle plates at intervals along the circumferential direction;
threaded blind holes which are in one-to-one correspondence with the counter bores are formed in the upper portion of the second turbine shaft at intervals along the circumferential direction;
the second positioning screw penetrates through a counter bore in the second-stage baffle plate, is installed in a threaded blind hole of the second turbine shaft in a threaded mode, and fixedly connects the second-stage baffle plate with the second turbine shaft.
Preferably, the fixing frame is a U-shaped frame;
the lower part of the power transmission device is fixedly nested in the U-shaped positioning groove of the fixing frame.
Further preferably, the coaxial reverse rotation two-stage turbine device for attenuating the energy of the tail flame emitted by the missile further comprises: a plurality of third set screws;
mounting holes corresponding to the third positioning screws one by one are formed in the longitudinal supports on the two sides of the fixing frame at intervals;
threaded blind holes which are in one-to-one correspondence with the mounting holes are formed in the peripheral side wall of the shell;
and after the third positioning screw penetrates through the corresponding mounting hole on the fixing frame, the third positioning screw is installed in the threaded blind hole on the shell in a threaded manner, so that the power transmission device is fixedly connected with the fixing frame.
The coaxial reverse rotation two-stage turbine device for weakening the energy of the missile launching tail flame provided by the invention guides the jet flow of the missile launching tail flame by the guide cone, changes the direction of the jet flow once, the jet flow guided by the guide cone acts on the first-stage turbine blades to drive the first-stage turbine to rotate, so that the secondary change of the direction of the jet flow is realized, the first-stage turbine is driven by the power transmission device after rotating to drive the second-stage turbine to rotate in the opposite direction, the second-stage turbine blades act to realize the tertiary change of the direction of the jet flow, the change of the direction of the jet flow every time can play the role of dispersing the energy of the jet flow and reducing the flow speed of the jet flow of the tail flame, meanwhile, the vector direction of partial tail flame jet flow is changed, the energy field of the tail flame jet flow is reduced, the quantity of stone impurities which can be rolled up by the tail flame jet flow is reduced, the initial kinetic energy of the impurities in the tail flame jet flow is weakened, and the damage to surrounding personnel and equipment is reduced or even avoided.
The coaxial reverse rotation two-stage turbine device for weakening the energy of the tail flame emitted by the missile has the advantages of simple structure, reasonable design, convenience in use and the like, and the energy is weakened and the damage to surrounding personnel and equipment is reduced by changing the direction of the tail flame jet flow for multiple times.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the disclosure.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the invention and together with the description, serve to explain the principles of the invention.
In order to more clearly illustrate the embodiments or technical solutions in the prior art of the present invention, the drawings used in the description of the embodiments or prior art will be briefly described below, and it is obvious for those skilled in the art that other drawings can be obtained based on these drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a coaxial reverse rotation two-stage turbine device for reducing the energy of a missile launching tail flame, provided by the disclosed embodiment of the invention;
FIG. 2 is a schematic diagram of the application of a coaxial reverse rotation two-stage turbine device for reducing the energy of the tail flame of the missile according to the disclosed embodiment of the invention.
Detailed Description
Reference will now be made in detail to the exemplary embodiments, examples of which are illustrated in the accompanying drawings. When the following description refers to the accompanying drawings, like numbers in different drawings represent the same or similar elements unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Rather, they are merely examples of apparatus consistent with certain aspects of the invention, as detailed in the appended claims.
When the missile is launched in the past, tail flame jet flow launched by the missile rapidly extends outwards to form a vortex, a large amount of impurities such as stones can be curled, the impurities are scattered at a high speed in a launching field, and surrounding personnel and equipment are easily damaged. In the past, researchers have tried to reduce the damage by using a blocking method, that is, a barrier, such as a steel plate, is erected on the ground, and the barrier blocks the scattered impurities, such as stones, but the effect is general. Therefore, in the present embodiment, the damage is reduced by reducing the energy of the tail flame jet, and the amount of the foreign matter such as stones to be rolled up can be greatly reduced by reducing the energy of the tail flame jet.
Based on the idea of reducing the tail flame jet flow energy, the embodiment designs a coaxial reverse rotation two-stage turbine device for reducing the tail flame energy emitted by the missile, and referring to fig. 1, the device mainly comprises a guide cone 1, a first-stage turbine 2, a second-stage turbine 3, a power transmission device 4 and a fixed frame 5.
Referring to fig. 1, the first-stage turbine 2 is mainly composed of a first-stage turbine shaft 21, a first-stage baffle 23, and a plurality of first-stage turbine blades 22, wherein the diameter of the upper part of the first-stage turbine shaft 21 is larger than the diameter of the lower part of the first-stage turbine shaft 21, a plurality of mounting grooves are arranged on the side wall of the upper part of the first-stage turbine shaft 21 at intervals, the first-stage turbine blades 22 correspond to the mounting grooves on the side wall of the first-stage turbine shaft 21 one by one, each first-stage turbine blade 22 is arranged in the corresponding mounting groove, the first-stage baffle 23 is sleeved outside the first-stage turbine shaft 21, and is fixedly connected with the lower end surface of the upper part of the first-stage turbine shaft 21, the guide cone 1 is positioned above the first-stage turbine 2, the lower end of the guide cone 1 is fixedly connected with the upper end of the first-stage turbine shaft 21, and the lower end surface of the guide cone 1 and the upper end surface of the first-stage baffle 23 clamp the first-stage turbine blades 22 and limit the first-stage turbine blades in the corresponding mounting grooves.
The structure of the secondary turbine 3 is substantially the same as that of the primary turbine 2, and referring to fig. 1, the secondary turbine 3 is mainly composed of a secondary turbine shaft 31, a secondary baffle 33 and a plurality of secondary turbine blades 32, wherein a mounting hole penetrating through the secondary turbine shaft 31 is arranged in the center, the secondary turbine shaft 31 is sleeved outside the lower part of the primary turbine shaft 21 through the mounting hole, the diameter of the upper part of the secondary turbine shaft 31 is larger than that of the lower part of the secondary turbine shaft 31, a plurality of mounting grooves are arranged on the upper side wall of the secondary turbine shaft 31 at intervals, the secondary turbine blades 32 are in one-to-one correspondence with the mounting grooves on the side wall of the secondary turbine shaft 32, each secondary turbine blade 32 is mounted in the corresponding mounting groove, the secondary baffle 33 is sleeved outside the secondary turbine shaft 21, the secondary baffle 33 is fixedly connected with the lower end face of the upper part of the secondary turbine shaft 31, and the secondary turbine blades 32 are clamped by the upper end face of the secondary baffle 33 and the lower end face of the primary baffle 23 And tightly limiting in the corresponding mounting groove.
The power transmission device 4 is mainly used for transmitting force between the first-stage turbine 2 and the second-stage turbine 3, and particularly, referring to fig. 1, the power transmission device 4 is located below the second-stage turbine 3, a power input end of the power transmission device 4 is in driving connection with the first-stage turbine shaft 21, a power output end of the power transmission device 4 is in driving connection with the second-stage turbine shaft 31, and the first-stage turbine 2 can drive the second-stage turbine 3 to rotate reversely after rotating through the transmission effect of the power transmission device 4. The fixed mount 5 is located below the power transmission device 4 and is fixedly connected with the power transmission device 4.
The coaxial reverse two-stage turbine device comprises a guide cone 1, a first-stage turbine 2, a second-stage turbine 3, a power transmission device 4 and a fixed frame 5 in sequence from top to bottom, wherein the fixed frame 5 is used for integrally supporting the coaxial reverse two-stage turbine device, when the coaxial reverse two-stage turbine device is used, the fixed frame 5 is fixedly arranged on the ground, the coaxial reverse two-stage turbine device mainly reduces the energy of tail flame jet flow by the guide cone 1, the first-stage turbine 2, the second-stage turbine 3 and the power transmission device 4, the specific working process is shown in figure 2, when a missile A launches, the guide cone 1 changes the direction of first air flow of high-speed tail flame jet flow sprayed from the tail of the missile A, the tail flame jet flow acts on first-stage turbine blades 22 along the surface of the guide cone 1 and pushes the first-stage turbine 2 to rotate, the direction of the flow field of the tail flame jet flow is changed for the second time, the first-stage turbine, the secondary turbine shaft 31 is driven to rotate reversely by the transmission of the power transmission device 4, and then the secondary turbine blades 32 are driven to rotate, so that three changes of the jet flow direction are realized, the purpose of dispersing jet flow energy can be achieved by changing the jet flow direction every time, the flow speed of tail flame jet flow is reduced, the vector direction of partial tail flame jet flow is changed, the energy field of the tail flame jet flow is reduced, the amount of sundries which can be rolled up by the tail flame jet flow is reduced, the initial kinetic energy of the sundries in the tail flame jet flow is weakened, and the damage to surrounding personnel and equipment is reduced or even avoided.
The structure of the power transmission device 4 in the above coaxial reverse rotation two-stage turbine device can be selected from various structures as long as the power transmission between the first-stage turbine 2 and the second-stage turbine 3 can be realized, preferably, the reverse motion between the second-stage turbine 3 and the first-stage turbine 2 is realized through the transmission of the power transmission device 4, the embodiment provides a specific structure of the power transmission device 4, referring to fig. 1, the power transmission device 4 mainly comprises a housing 41, a bottom plate 42, a first large bevel gear 43, a second large bevel gear 44 and a plurality of small bevel gears 45, wherein the lower end of the housing 41 is open, the upper end of the housing 41 is provided with a mounting hole, the bottom plate 42 is mounted at the lower end opening of the housing 41 in a sealing manner and fixed through screws, the bottom plate 42 and the housing 41 enclose a cavity, the first large bevel gear 43 is located in the cavity, and fixedly sleeved outside the second-stage turbine shaft 31, the second large bevel gear 44 is positioned in the cavity and arranged below the first large bevel gear 43, the second large bevel gear 44 is fixedly sleeved outside the primary turbine shaft 21, the plurality of small bevel gears 45 are positioned between the first large bevel gear 43 and the second large bevel gear 44 and are respectively meshed with the first large bevel gear 43 and the second large bevel gear 44, and each small bevel gear 45 is rotatably connected with the side wall of the shell 41.
The specific working principle of the power transmission device 4 is as follows: when the one-level turbine shaft 21 rotates, the second large bevel gear 44 fixedly sleeved outside the first large bevel gear can be driven to rotate, when the second large bevel gear 44 rotates, the plurality of small bevel gears 45 above the second large bevel gear 44 are used for transmission, the first large bevel gear 43 can be driven to rotate reversely, so that the second-level turbine shaft 31 fixedly nested in the first large bevel gear 43 is driven to rotate reversely, namely, the whole second-level turbine 3 is used for rotating reversely, and the rotation power transmission between the first-level turbine 2 and the second-level turbine 3 is completed.
In order to facilitate the position fixing and limiting of the primary turbine shaft 21, as a modification of the technical solution, referring to fig. 1, a limiting groove is provided in the center of the bottom plate 42, and the lower end of the primary turbine shaft 21 is rotatably limited in the limiting groove.
In the above solution, the connection manner among the first-stage blocking piece 23, the first-stage turbine shaft 21 and the guide cone 1 can be selected from various manners, as long as the fixed connection among the three can be realized, the present embodiment provides a structure form with relatively simple structure and convenient assembly, referring to fig. 1, a plurality of first positioning screws 6 are further provided in the coaxial reverse rotation two-stage turbine device, wherein the first-stage blocking piece 23 is circumferentially provided with countersunk holes corresponding to the first positioning screws 6 one to one at intervals, the upper portion of the first turbine shaft 21 is circumferentially provided with through holes corresponding to the countersunk holes one to one at intervals, the lower end surface of the guide cone 1 is circumferentially provided with blind threaded holes corresponding to the through holes one to one at intervals, after the first positioning screws 6 sequentially pass through the corresponding countersunk holes on the first-stage blocking piece 23 and the corresponding through holes on the first turbine shaft 21, the threads are installed in the corresponding blind threaded holes on the guide cone 1, the first-stage baffle plate 23, the first turbine shaft 21 and the guide cone 2 are fixedly connected.
In the above solution, the connection manner between the secondary baffle 33 and the second turbine shaft 31 may be selected from multiple manners, as long as the two can be fixedly connected, and this embodiment provides a structural form with a relatively simple structure and convenient assembly, referring to fig. 1, a plurality of second positioning screws 7 are further provided in the coaxial reverse rotation two-stage turbine device, wherein the secondary baffle 33 is provided with countersunk holes at intervals along the circumferential direction, the countersunk holes are in one-to-one correspondence with the second positioning screws 7, the threaded blind holes are provided at intervals along the circumferential direction on the upper portion of the second turbine shaft 31, the second positioning screws 7 pass through the corresponding countersunk holes on the secondary baffle 33, the threads are installed in the threaded blind holes corresponding to the second turbine shaft 31, and the secondary baffle 33 and the second turbine shaft 31 are fixedly connected.
In the above embodiment, the structure of the fixing frame 5 can be selected in various ways as long as the supporting and ground fixing effects can be realized, in this embodiment, a U-shaped frame is adopted as the fixing frame 5, the lower part of the power transmission device 4 is fixedly nested in a U-shaped positioning groove of the fixing frame 5, and the fixing and supporting of the power transmission device 4 are realized through the fixing frame 5.
The fixing mode between the power transmission device 4 and the fixing frame 5 may be a screw mode, specifically referring to fig. 1, a plurality of third positioning screws 8 are arranged in the damping type two-stage turbine device, mounting holes corresponding to the third positioning screws 8 one to one are arranged on longitudinal supports on two sides of the fixing frame 5 at intervals, threaded blind holes corresponding to the mounting holes one to one are arranged on the peripheral side wall of the housing 41 in the power transmission device 4, and after the third positioning screws 8 penetrate through the corresponding mounting holes on the fixing frame 5, the third positioning screws are threadedly mounted in the threaded blind holes on the housing 41 to fixedly connect the power transmission device 4 and the fixing frame 5.
In practice, by using the coaxial reverse two-stage turbine device, when the missile launches, after the high-speed tail flame jet flows through the coaxial reverse two-stage turbine device, the flow speed of the tail flame jet flow of the missile is reduced, the vector direction of partial tail flame jet flow is changed, the energy field of the tail flame jet flow is reduced, and the distribution of the energy field of the tail flame jet flow is changed, so that the amount of impurities curled by the tail flame jet flow is reduced, the initial kinetic energy of the impurities in the tail flame jet flow is weakened, and further, the damage to personnel and equipment in the launching site is reduced.
Other embodiments of the invention will be apparent to those skilled in the art from consideration of the specification and practice of the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of the invention following, in general, the principles of the invention and including such departures from the present disclosure as come within known or customary practice within the art to which the invention pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the invention being indicated by the following claims.
It is to be understood that the present invention is not limited to what has been described above, and that various modifications and changes may be made without departing from the scope thereof. The scope of the invention is limited only by the appended claims.
Claims (7)
1. A coaxial reverse rotation two-stage turbine device for weakening the energy of tail flame emitted by a missile, which is characterized by comprising: the device comprises a guide cone (1), a first-stage turbine (2), a second-stage turbine (3), a power transmission device (4) and a fixed frame (5);
the first stage turbine (2) comprises: a first-stage turbine shaft (21), a first-stage baffle plate (23) and a plurality of first-stage turbine blades (22);
the diameter of the upper part of the primary turbine shaft (21) is larger than that of the lower part of the primary turbine shaft (21), and a plurality of mounting grooves are arranged on the side wall of the upper part of the primary turbine shaft (21) at intervals;
the first-stage turbine blades (22) correspond to mounting grooves in the side wall of the first-stage turbine shaft (21) one by one, and each first-stage turbine blade (22) is mounted in the corresponding mounting groove;
the primary baffle plate (23) is sleeved outside the primary turbine shaft (21) and is fixedly connected with the lower end face of the upper part of the primary turbine shaft (21);
the guide cone (1) is positioned above the first-stage turbine (2), and the lower end of the guide cone (1) is fixedly connected with the upper end of the first-stage turbine shaft (21);
the two-stage turbine (3) comprises: a secondary turbine shaft (31), a secondary baffle (33), and a plurality of secondary turbine blades (32);
the center of the secondary turbine shaft (31) is provided with a through mounting hole, the secondary turbine shaft (31) is sleeved outside the lower part of the primary turbine shaft (21) through the mounting hole, the diameter of the upper part of the secondary turbine shaft (31) is larger than that of the lower part of the secondary turbine shaft (31), and a plurality of mounting grooves are arranged on the side wall of the upper part of the secondary turbine shaft (31) at intervals;
the secondary turbine blades (32) correspond to mounting grooves in the side wall of the secondary turbine shaft (32) one by one, and each secondary turbine blade (32) is mounted in the corresponding mounting groove;
the secondary baffle plate (33) is sleeved outside the secondary turbine shaft (21), and the secondary baffle plate (33) is fixedly connected with the lower end face of the upper part of the secondary turbine shaft (31);
the power transmission device (4) is positioned below the secondary turbine (3), the power input end of the power transmission device (4) is in driving connection with the primary turbine shaft (21), and the power output end of the power transmission device (4) is in driving connection with the secondary turbine shaft (31);
the fixing frame (5) is positioned below the power transmission device (4) and is fixedly connected with the power transmission device (4).
2. The coaxial, counter-rotating, two-stage turbine device for attenuating the energy of a missile-launching tail flame as in claim 1, wherein the power transmission means (4) comprises: the gear transmission mechanism comprises a shell (41), a bottom plate (42), a first large bevel gear (43), a second large bevel gear (44) and a plurality of small bevel gears (45);
the lower end of the shell (41) is open, and the upper end of the shell is provided with a mounting hole;
the bottom plate (42) is plugged and installed at an opening at the lower end of the shell (41) and forms a cavity together with the shell (41);
the first large bevel gear (43) is positioned in the cavity and fixedly sleeved outside the secondary turbine shaft (31);
the second large bevel gear (44) is positioned in the cavity and arranged below the first large bevel gear (43), and is fixedly sleeved outside the primary turbine shaft (21);
the small bevel gears (45) are located between the first large bevel gear (43) and the second large bevel gear (44) and are meshed with the first large bevel gear (43) and the second large bevel gear (44) respectively, and each small bevel gear (45) is rotatably connected with the side wall of the shell (41).
3. The coaxial reverse rotation two-stage turbine device for attenuating missile-launching tail flame energy as in claim 2, wherein a limiting groove is formed in the center of the bottom plate (42), and the lower end of the first-stage turbine shaft (21) is rotatably limited in the limiting groove.
4. The coaxial, counter-rotating, two-stage turbine apparatus for attenuating missile launch tail flame energy of claim 1, further comprising: a plurality of first set screws (6);
countersunk holes which are in one-to-one correspondence with the first positioning screws (6) are formed in the first-stage blocking pieces (23) at intervals along the circumferential direction;
through holes which correspond to the countersunk holes one by one are formed in the upper part of the first turbine shaft (21) at intervals along the circumferential direction;
threaded blind holes which are in one-to-one correspondence with the through holes are formed in the lower end face of the flow guide cone (1) at intervals along the circumferential direction;
and the first positioning screw (6) is arranged in a threaded blind hole on the diversion cone (1) after sequentially penetrating through a countersunk hole on the first-level baffle plate (23) and a through hole on the first turbine shaft (21), and is fixedly connected with the first-level baffle plate (23), the first turbine shaft (21) and the diversion cone (2).
5. The coaxial, counter-rotating, two-stage turbine apparatus for attenuating missile launch tail flame energy of claim 1, further comprising: a plurality of second set screws (7);
countersunk holes which are in one-to-one correspondence with the second positioning screws (7) are formed in the secondary baffle plates (33) at intervals along the circumferential direction;
threaded blind holes which are in one-to-one correspondence with the counter bores are formed in the upper portion of the second turbine shaft (31) at intervals along the circumferential direction;
the second positioning screw (7) penetrates through a countersunk hole in the secondary baffle plate (33), is installed in a threaded blind hole of the second turbine shaft (31) in a threaded mode, and fixedly connects the secondary baffle plate (33) with the second turbine shaft (31).
6. The coaxial, counter-rotating, two-stage turbine device for attenuating the energy of a missile-launching tail flame according to claim 1, wherein the fixed mount (5) is a U-shaped mount;
the lower part of the power transmission device (4) is fixedly nested in the U-shaped positioning groove of the fixing frame (5).
7. The coaxial, counter-rotating, two-stage turbine arrangement for attenuating missile launch tail flame energy of claim 6, further comprising: a plurality of third set screws (8);
mounting holes which correspond to the third positioning screws (8) one by one are arranged on the longitudinal supports on the two sides of the fixing frame (5) at intervals;
threaded blind holes which are in one-to-one correspondence with the mounting holes are formed in the peripheral side wall of the shell (41);
and after the third positioning screw (8) penetrates through the corresponding mounting hole on the fixed frame (5), the third positioning screw is mounted in the threaded blind hole on the shell (41) in a threaded manner, so that the power transmission device (4) is fixedly connected with the fixed frame (5).
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| CN202110434342.4A CN113202563B (en) | 2021-04-22 | 2021-04-22 | Coaxial reverse rotation two-stage turbine device for weakening missile launching tail flame energy |
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| CN202110434342.4A CN113202563B (en) | 2021-04-22 | 2021-04-22 | Coaxial reverse rotation two-stage turbine device for weakening missile launching tail flame energy |
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| CN113202563B CN113202563B (en) | 2022-08-16 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115388721A (en) * | 2022-10-26 | 2022-11-25 | 中国航空工业集团公司沈阳空气动力研究所 | Control device for drag reduction and thrust augmentation of bottom of carrier rocket |
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| GB872600A (en) * | 1957-08-30 | 1961-07-12 | Bristol Siddeley Engines Ltd | Improvements in combustion ducts |
| GB2083953A (en) * | 1980-08-27 | 1982-03-31 | Ferranti Ltd | Air turbine generators for missiles |
| CN109538378A (en) * | 2019-01-07 | 2019-03-29 | 西安交通大学 | A kind of processing system of engine gas jet stream wake flame |
| CN112377267A (en) * | 2020-11-30 | 2021-02-19 | 中国电子科技集团公司第十六研究所 | Self-cooling high-speed ram air turbine generator |
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| GB739417A (en) * | 1953-03-14 | 1955-10-26 | Energa | Improvements in rocket motors |
| GB872600A (en) * | 1957-08-30 | 1961-07-12 | Bristol Siddeley Engines Ltd | Improvements in combustion ducts |
| GB2083953A (en) * | 1980-08-27 | 1982-03-31 | Ferranti Ltd | Air turbine generators for missiles |
| CN109538378A (en) * | 2019-01-07 | 2019-03-29 | 西安交通大学 | A kind of processing system of engine gas jet stream wake flame |
| CN112377267A (en) * | 2020-11-30 | 2021-02-19 | 中国电子科技集团公司第十六研究所 | Self-cooling high-speed ram air turbine generator |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115388721A (en) * | 2022-10-26 | 2022-11-25 | 中国航空工业集团公司沈阳空气动力研究所 | Control device for drag reduction and thrust augmentation of bottom of carrier rocket |
| CN115388721B (en) * | 2022-10-26 | 2022-12-20 | 中国航空工业集团公司沈阳空气动力研究所 | Control device for drag reduction and thrust augmentation of bottom of carrier rocket |
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| Publication number | Publication date |
|---|---|
| CN113202563B (en) | 2022-08-16 |
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