CN204532577U - Supersonic airliner one has operatic tunes rocket thrust chamber - Google Patents
Supersonic airliner one has operatic tunes rocket thrust chamber Download PDFInfo
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- CN204532577U CN204532577U CN201520016611.5U CN201520016611U CN204532577U CN 204532577 U CN204532577 U CN 204532577U CN 201520016611 U CN201520016611 U CN 201520016611U CN 204532577 U CN204532577 U CN 204532577U
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- operatic tunes
- thrust chamber
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- body portion
- ring
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Abstract
The utility model relates to one operatic tunes rocket thrust chamber, belongs in 70%-75% hydrogen peroxide/aviation kerosine and presses staged combustion rocket engine.In order to develop the rocket motor meeting supersonic airliner usage requirement, the utility model adopts the thrust chamber technological scheme such as operatic tunes Tipple Bottom head construction, two kinds of gas-liquid spray unit, bundled tube body portion structures.Major advantage is that thrust chamber combustion temperature is very low, the cooling of thrust chamber body portion is very reliable, enters the oxygen rich air temperature of thrust chamber less than 400 DEG C, and the operatic tunes can effective vibration damping, greatly reduce technical difficulty, possess the condition using less cost and short period to develop supersonic airliner rocket motor.The utility model is mainly used in supersonic airliner, is also applicable to rocket airplane, space shuttle, interstellar vehicle, carrier rocket, liquid missile etc.
Description
Technical field
The utility model relates to the hydrogen peroxide/kerosene rocket motor of aircraft.
Background technique
Aircarrier aircraft is safe and applicable, but more than ten hours consuming time of intercontinental long voyage, passenger is more tired.Associate the benefit of high ferro and motor-car, long voyage aircarrier aircraft also should speedup about a times, becomes with the supersonic airliner of 2-3 times of subsonic cruise.
As far back as 1976, Europe, with regard to Yan Kai and number supersonic airliner, was the passenger plane advancing aft swept wings with high thrust aero-jet engine.There is the shortcomings such as safe not, fault is more, maintenance cost is high, T-O noise is large in this aircraft, after there is airplane crash in 2000 3 years retired.
Nearest America and Europe is new generation supersonic airliner again." N+2 " commercial supersonic airliner of american lockheed-LMT's research and development, can hold 80 passengers, have employed new power system (not quite clear).Aerion air technology company of the U.S. also cooperates with European airbus group, and development only has the AS2 supersonic speed commercial affairs jet plane of 12 passengers, adopts the wing design of minimizing 20% resistance, estimates to take a flight test for 2019.
The supersonic airliner scheme that I proposes sets up a rocket motor at airplane tail group, forms two propulsion system with the aero-jet engine under wing.Rise to about 20000 meters new cruising altitudes in cruising altitude conventional from about ten thousand metres and accelerate to the after-stage of 2-3 times of velocity of sound, starting rocket motor and carry out two propelling.The major advantage of the program is can the former state of the art of more reservation aircraft, take off, early stage climb and the flight characteristic of landing station constant, occupant's number can be some more.
The rocket motor of supersonic airliner require to have with aero-jet engine close safe and reliable, vibrate the features such as little, the life-span is grown, can reuse many times, working service convenience, good economy performance, the propellant agent of use will be convenient to filling vehicle filling.In addition, the supersonic airliner most of the time, in the high-altitude flight of rarefaction of air, also needs to provide the source of the gas regulating main cabin amount of oxygen, pressure, temperature and humidity.All do not have both at home and abroad at present to meet these rocket motor required.Although hydrogen peroxide/kerosene rocket motor is used on military aircraft already, high concentration 85%-98% hydrogen peroxide is not too safe, less.I has " a kind of intermediate concentration hydrogen peroxide/kerosene firing chamber without the catalytic bed " utility model patent (ZL 201320842845.6) got permission, improve Security and usability, but this dual-use Small Combustion room, without vibration damping facility, can not be used on the liquid propellant rocket engine of supersonic airliner.
Summary of the invention
At home and abroad all do not have at present for the rocket motor being applicable to supersonic airliner, the firing chamber of above-mentioned patent is without vibration damping facility, in order to develop the rocket motor meeting supersonic airliner usage requirement, the one that the utility model provides as this motor major component has operatic tunes rocket thrust chamber.
Rocket thrust chamber of the present utility model uses low concentration 70%-75% hydrogen peroxide as oxygenant, and nontoxic, colourless, odorlessness is the environment protection chemical product that corrosivity is little.It is safe for being undertaken producing, transport, store and using by National Standard of the People's Republic of China GB1616-2003.Good re-generatively cooled agent, can not carbon deposit coking, also not easily produce thrust chamber inner surface heat tired.Freezing point-40 DEG C-32 DEG C, boiling point 125 DEG C-129 DEG C, can use throughout the year.1 kilogram of price 6 yuans of technical grade 70% hydrogen peroxide, more cheaply.Density is large, at the density 1.2867-1.3103g/cm of 25 DEG C
3.Decomposition temperature is low, the complete decomposition temperature under barometric pressure 266.8 DEG C-388.9 DEG C, the complete decomposition temperature of 15MPa pressure 321.6 DEG C-393.9 DEG C.
Rocket thrust chamber of the present utility model uses aviation kerosine as fuel, and mainly No. 3 jet fuels or No. 2 jet fuels, this is identical with the fuel of aero-jet engine.
The fire lighter that rocket thrust chamber of the present utility model uses is spontaneous combustion kerosene, is made up of, refers to my patent application CN102863994A kerosene, primary catalyst, secondary catalysts and solvents.Spontaneous combustion kerosene enters thrust chamber prior to aviation kerosine 1-3 second, contacts and spontaneous ignition with the initial oxygen rich air containing undecomposed hydrogen peroxide.
Supersonic airliner one of the present utility model is made up of head and body portion operatic tunes rocket thrust chamber, head comprises the interior end, oxygen rich air nozzle, the middle end, outer bottom, there is the fitting seat of oxygen rich air inlet duct, the operatic tunes, liquid trap ring, filter screen and kerosene inlet connection mouth, body portion comprises hydrogen peroxide inlet duct, liquid trap ring, filter screen, diffuser shell, mounting flange, jet pipe extension, herringbone ring, varying cross-section duct, converging portion shell, cylindrical section shell, liquid trap ring, hydrogen peroxide outlet port pipe and connecting ring, except jet pipe extension be connect with bolt except remaining parts be all welded and fixed.The interior end, oxygen rich air nozzle, the middle end, outer bottom and operatic tunes composition have the Tipple Bottom head construction of the operatic tunes, have the kerosene inclined hole and straight hole that form two kinds of gas-liquid spray unit with oxygen rich air nozzle the interior end, many varying cross-section ducts circumferentially arrange the bundled tube body portion structure of assembly welding one-tenth 70%-75% hydrogen peroxide as re-generatively cooled agent.
The operatic tunes circumferentially has the quantity two kind straight troughs identical with width, the degree of depth and arc length large be the dark operatic tunes, the degree of depth and arc length little be the shallow operatic tunes, alternately, the position on the operatic tunes rib between the operatic tunes in corresponding at the end and the middle end has radial flute profile kerosene hole to two kinds of operatic tunes.
The oxygen rich air nozzle of gas-liquid spray unit is straight hole type gas nozzle, becomes as a whole by concentric circle compact arrangement with the interior end with the middle end, has the kerosene spray orifice identical with number of nozzle the end in the small space between nozzle, and outmost turns is straight hole is inclined holes with all the other.
All varying cross-section ducts of bundled tube body portion structure outside the root at two ends and the corresponding site of diffuser shell and cylindrical section shell all have slotted hole and radial slotted hole.
Operatic tunes groove external diameter after direct-connected T-Ring formation head is connected with body portion equals thrust chamber cylindrical section internal diameter, and the operatic tunes groove internal diameter after connecting ring formation head is connected with body portion is not less than thrust chamber cylindrical section internal diameter.
Supersonic airliner one of the present utility model has operatic tunes rocket thrust chamber major advantage and beneficial effect:
(1) rocket thrust chamber combustion temperature of the present utility model is than existing liquid oxygen/kerosene and liquid oxygen/liquid hydrogen thrust chamber combustion temperature 3250 DEG C-3400 DEG C low 1138 DEG C-1442 DEG C more than, bundled tube body portion without welding slag in and 70%-75% hydrogen peroxide cooling tube that cooling performance is good large with flow is very reliable, add enter thrust chamber oxygen rich air temperature less than 400 DEG C, the operating conditions of this kind of rocket thrust chamber can be made to obtain thorough improvement, greatly reduce technical difficulty, possess the condition using less cost and short period to develop supersonic airliner rocket motor.
(2) rocket thrust chamber of the present utility model is provided with the depth two kinds of operatic tunes suppressing somatic sypermutation and vibration damping, outmost turns oxidize nozzle and corresponding fuel straight hole is adopted to reduce the temperature of the outer combustion gas Jiong Liu district of operatic tunes entrance or transition zone, and with the fuel of radially hole flowing in operatic tunes rib, outer cooling is carried out to the rib place of being heated, operatic tunes reliably working can be guaranteed, effectively can reduce the mechanical vibration of supersonic airliner rocket motor.
The utility model relates to one operatic tunes rocket thrust chamber, uses real nontoxic storable propellant 70%-75% hydrogen peroxide/aviation kerosine, belongs to a kind of major component of middle pressure staged combustion rocket engine.Mainly be applicable to supersonic airliner, be also applicable to rocket airplane, space shuttle, interstellar vehicle, carrier rocket, liquid missile etc.
Accompanying drawing explanation
Fig. 1 is a kind of head worm's eye view having operatic tunes rocket thrust chamber of the utility model, i.e. the layout plan of spray unit and the operatic tunes.
Fig. 1-1 is head worm's eye view.
Fig. 1-2 is the A-A sectional drawing of Fig. 1-1.
Fig. 1-3 is B-B sectional drawings of Fig. 1-1.
Fig. 2 is thrust chamber head front view.
Fig. 3 is thrust chamber body portion front view.
Fig. 4 is a kind of thrust chamber structure diagram that head and body portion link into an integrated entity.
Embodiment
Comprise Fig. 1-1, Fig. 1, Fig. 2, Fig. 3 and Fig. 4 of Fig. 1-2 and Fig. 1-3 are a kind of preferred embodiment having operatic tunes rocket thrust chamber of the utility model.
As shown in Figures 1 to 4, supersonic airliner one is made up of head and body portion operatic tunes rocket thrust chamber, head comprises the interior end 1, oxygen rich air nozzle 2, the middle end 3, outer bottom 4, there is the fitting seat 5 of oxygen rich air inlet duct, the operatic tunes 6, liquid trap ring 7, filter screen 8 and kerosene inlet connection mouth 9, body portion comprises hydrogen peroxide inlet duct 10, liquid trap ring 11, filter screen 12, diffuser shell 13, mounting flange 14, jet pipe extension 15, herringbone ring 16, varying cross-section duct 17, converging portion shell 18, cylindrical section shell 19, liquid trap ring 20, hydrogen peroxide outlet port pipe 21 and direct-connected T-Ring 22 or connecting ring 22A, except jet pipe extension 15 be connect with bolt except remaining parts be all welded and fixed.The interior end 1, oxygen rich air nozzle 2, the middle end 3, outer bottom 4 and the operatic tunes 6 composition have the Tipple Bottom head construction of the operatic tunes, the interior end 1 has the kerosene inclined hole 23 forming two kinds of gas-liquid spray unit with oxygen rich air nozzle 2 and straight hole 24, and many varying cross-section ducts 17 circumferentially arrange the bundled tube body portion structure of assembly welding one-tenth 70%-75% hydrogen peroxide as re-generatively cooled agent.
The operatic tunes 6 circumferentially has the quantity two kind straight troughs identical with width, the degree of depth and arc length large be the dark operatic tunes 25, the degree of depth and arc length little be the shallow operatic tunes 26, two kinds of operatic tunes alternately, the position on the operatic tunes rib between the operatic tunes in corresponding at the end 1 and the middle end 3 has radial flute profile kerosene hole 27.
The oxygen rich air nozzle 2 of gas-liquid spray unit is straight hole type gas nozzle, as a whole with middle 3 one-tenth, the end with the interior end 1 by concentric circle compact arrangement, have the kerosene spray orifice identical with number of nozzle the end 1 in small space between nozzle, outmost turns is straight hole 24 is inclined holes 23 with all the other.
All varying cross-section ducts 17 of bundled tube body portion structure outside the root at two ends and the corresponding site of diffuser shell 13 and cylindrical section shell 19 all have slotted hole 28 and radial slotted hole 29.
Direct-connected T-Ring 22 form head be connected with body portion after operatic tunes groove outer diameter D 1 equal thrust chamber cylindrical section internal diameter D, connecting ring 22A form head be connected with body portion after operatic tunes groove internal diameter D2 be not less than thrust chamber cylindrical section internal diameter D.
Claims (5)
1. supersonic airliner one is made up of head and body portion operatic tunes rocket thrust chamber, and head comprises the interior end (1), oxygen rich air nozzle (2), the middle end (3), outer bottom (4), there is the fitting seat (5) of oxygen rich air inlet duct, the operatic tunes (6), liquid trap ring (7), filter screen (8) and kerosene inlet connection mouth (9), body portion comprises hydrogen peroxide inlet duct (10), liquid trap ring (11), filter screen (12), diffuser shell (13), mounting flange (14), jet pipe extension (15), herringbone ring (16), varying cross-section duct (17), converging portion shell (18), cylindrical section shell (19), liquid trap ring (20), hydrogen peroxide outlet port pipe (21) and direct-connected T-Ring (22) or connecting ring (22A), except jet pipe extension (15) be connect with bolt except remaining parts be all welded and fixed, it is characterized in that: the described interior end (1), oxygen rich air nozzle (2), the middle end (3), outer bottom (4) and the operatic tunes (6) composition have the Tipple Bottom head construction of the operatic tunes, have the kerosene inclined hole (23) and straight hole (24) that form two kinds of gas-liquid spray unit with oxygen rich air nozzle (2) the interior end (1), many varying cross-section ducts (17) circumferentially arrange the bundled tube body portion structure of assembly welding one-tenth 70%-75% hydrogen peroxide as re-generatively cooled agent.
2. supersonic airliner one according to claim 1 has operatic tunes rocket thrust chamber, it is characterized in that: the described operatic tunes (6) circumferentially has two kinds of straight troughs that quantity is identical with width, the degree of depth and the large straight trough of arc length are the dark operatic tunes (25), the degree of depth and the little straight trough of arc length are the shallow operatic tunes (26), alternately, the position on the operatic tunes rib between the operatic tunes in correspondence between the end (1) and the middle end (3) has radial flute profile kerosene hole (27) to two kinds of operatic tunes.
3. supersonic airliner one according to claim 1 has operatic tunes rocket thrust chamber, it is characterized in that: the oxygen rich air nozzle (2) of described gas-liquid spray unit is straight hole type gas nozzle, become as a whole with the interior end (1) with the middle end (3) by concentric circle compact arrangement, in small space between nozzle, the end (1) has the kerosene spray orifice identical with number of nozzle, outmost turns be straight hole (24) and all the other are inclined hole (23).
4. supersonic airliner one according to claim 1 has operatic tunes rocket thrust chamber, it is characterized in that: all varying cross-section ducts (17) of described bundled tube body portion structure outside the root at two ends and the corresponding site of diffuser shell (13) and cylindrical section shell (19) all have slotted hole (28) and radial slotted hole (29).
5. supersonic airliner one according to claim 1 has operatic tunes rocket thrust chamber, it is characterized in that: described direct-connected T-Ring (22) form head be connected with body portion after operatic tunes groove outer diameter D 1 equal thrust chamber cylindrical section internal diameter D, connecting ring (22A) form head be connected with body portion after operatic tunes groove internal diameter D2 be not less than thrust chamber cylindrical section internal diameter D.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520016611.5U CN204532577U (en) | 2015-01-12 | 2015-01-12 | Supersonic airliner one has operatic tunes rocket thrust chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520016611.5U CN204532577U (en) | 2015-01-12 | 2015-01-12 | Supersonic airliner one has operatic tunes rocket thrust chamber |
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| Publication Number | Publication Date |
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| CN204532577U true CN204532577U (en) | 2015-08-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520016611.5U Expired - Fee Related CN204532577U (en) | 2015-01-12 | 2015-01-12 | Supersonic airliner one has operatic tunes rocket thrust chamber |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104632467A (en) * | 2015-01-12 | 2015-05-20 | 葛明龙 | Rocket thrust chamber provided with acoustic cavity and applied to supersonic airliner and supply system thereof |
| CN112267956A (en) * | 2020-10-23 | 2021-01-26 | 贵州航天朝阳科技有限责任公司 | Combustion chamber of double-component liquid propellant rocket engine and combustion control method |
-
2015
- 2015-01-12 CN CN201520016611.5U patent/CN204532577U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104632467A (en) * | 2015-01-12 | 2015-05-20 | 葛明龙 | Rocket thrust chamber provided with acoustic cavity and applied to supersonic airliner and supply system thereof |
| CN112267956A (en) * | 2020-10-23 | 2021-01-26 | 贵州航天朝阳科技有限责任公司 | Combustion chamber of double-component liquid propellant rocket engine and combustion control method |
| CN112267956B (en) * | 2020-10-23 | 2021-08-27 | 贵州航天朝阳科技有限责任公司 | Combustion chamber of double-component liquid propellant rocket engine and combustion control method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| DD01 | Delivery of document by public notice |
Addressee: Ge Minglong Document name: Notification of Termination of Patent Right |
|
| DD01 | Delivery of document by public notice | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150805 Termination date: 20170112 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |