CN201083164Y - Turbine-rocket embedded type engine - Google Patents
Turbine-rocket embedded type engine Download PDFInfo
- Publication number
- CN201083164Y CN201083164Y CNU2007200149740U CN200720014974U CN201083164Y CN 201083164 Y CN201083164 Y CN 201083164Y CN U2007200149740 U CNU2007200149740 U CN U2007200149740U CN 200720014974 U CN200720014974 U CN 200720014974U CN 201083164 Y CN201083164 Y CN 201083164Y
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- CN
- China
- Prior art keywords
- rocket
- turbogenerator
- turbine
- engine
- embedded type
- 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.)
- Expired - Fee Related
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Abstract
An embedded turbo-rocket engine of the utility model relates to a propulsion system with of the combination of a turbine engine and a rocket engine. The utility model integrates the best working conditions of the turbine engine and the rocket engine into an engine cycle and provides an engine novel of a novel structure in which a turbine engine is provided with a hollow shaft and a rocket engine is embedded in an intake cone and the hollow shaft, based on the prior combination engine, which makes full use of the inner space of the turbine engine. The utility model has the advantages that the new embedded turbo-rocket engine has a compact structure, is convenient to assemble and disassemble, easy to maintain, high in reliability, large in thrust, long in shot range, simple in structure, light in weight and less in residue discharge.
Description
Technical field
The utility model relates to a kind of propulsion system by turbogenerator and rocket motor combination, the empty day round propulsion system that especially be applied to high-energy, become thrust, signal characteristic is low.
Background technique
Up to the present, for the non-constant width of flight envelope scope (height 0～40km or higher, flight Mach number from infrasound, stride sound, ultrasound velocity expands to hypersonic) hypersonic aircraft, therefore also do not have a kind of function of starting independently to finish the propelling task, proposed to utilize two or more cluster engines abroad altogether as the conception of hypersonic thrust power.
Advantage when the turbine-rocket motor combines turbogenerator and rocket motor and works independently makes and adopts the propulsion system of this motor can both obtain good propulsive performance under different flying conditions.But, before the present combined engine of studying places turbogenerator with rocket propellant, thereby increased the axial dimension of motor, bring difficulty for simultaneously powder charge, maintenance and the repeated use of rocket motor.
Therefore, on the basis of existing turbine-rocket combined engine technology, those skilled in the art be badly in need of providing a kind of structure characteristic that can make full use of combined engine, each motor of reasonable Arrangement the position, make engine structure compact more, more rationally, be convenient to maintenance and reusable novel turbine-rocket combined engine.
Summary of the invention
The purpose of this utility model provides a kind of turbine-rocket embedded type engine, it has, and compact structure, volume are little, in light weight, easy accessibility, be easy to safeguard, convenient reusable advantage.
In order to achieve the above object, the technical solution of the utility model is as follows:
A kind of turbine-rocket embedded type engine, form by turbogenerator 1 and rocket motor 3, the axle of turbogenerator 1 is a quill shaft, the axle front end is the turbogenerator inlet cone 2 of taper, rocket motor 3 is embedded in turbogenerator inlet cone 2 and the quill shaft, and guide-ring 4 is positioned at the rear end of turbogenerator inlet cone 2; The wheel disc of compression system 5 adopts key or bearing ways of connecting to be fixed on the axle, and the tooth-like or brush seal of combing is adopted in the front and back of compression system 5; Turbine rotor 7 adopts bolt or bearing ways of connecting to be fixed on the axle, its import and export and the inboard brush seal that adopts; Turbogenerator firing chamber 6 is between compression system 5 and turbine rotor 7; The closed rocket motor variable area nozzle 9 and the external casing of turbogenerator constitute turbogenerator jet pipe 8 jointly, and support plate 10 is connected with turbogenerator inlet cone 2 by riveted joint or welding or bolt or screw or pin.
Above-mentioned rocket motor 3 is solid propellant rocket or liquid propellant rocket engine; Above-mentioned compression system 5 is progression conventional gas compressor (being axial-flow compressor, centrifugal-flow compressor) gas compressor or rotary punching compression rotor seldom.
The beneficial effects of the utility model are as follows:
1) adopts less conventional gas compressor or the rotary punching compression rotor of progression, to reduce the overall dimensions and the weight of turbine-rocket embedded type engine;
2) have airbreathing motor (being turbogenerator) system, both can produce static thrust, can when cruising, accelerate to ultrasound velocity again;
3) the different propulsion system of starting during different operating conditions, specific impulse is big, and mobility is good;
4) change rocket motor and jet pipe parts conveniently, can realize quick repeated use.
Description of drawings
Fig. 1 is the structural representation of a kind of turbine of the present utility model-solid-rocket embedded type engine.
Fig. 2 is the structural representation of a kind of turbine of the present utility model-liquid rocket embedded type engine.
Among the figure: 1, turbogenerator, 2, the turbogenerator inlet cone, 3, rocket motor, 4, guide-ring, 5, compression system, 6, the turbogenerator firing chamber, 7, turbine rotor, 8, turbogenerator jet pipe, 9, the rocket motor variable area nozzle, 10, support plate.
Embodiment
Below in conjunction with accompanying drawing the utility model is done description in further detail:
As depicted in figs. 1 and 2, turbine-rocket embedded type engine of the present utility model is made up of turbogenerator 1 and solid (or liquid) rocket motor 3, turbogenerator 1 adopts the quill shaft design, the axle Front-end Design is tapered, turbogenerator inlet cone 2 before the axle is longer, both provided bigger charge space to alleviate engine weight simultaneously, played again the precompressed effect of air-flow.
Rocket motor 3 is embedded in the inlet cone 2 and quill shaft of turbogenerator, has effectively utilized the inner space of motor, and the jet nozzle fender plate is opened during work, relies on propellant combustion to produce thrust.
The working principle and the process of turbine-rocket embedded type engine of the present utility model are: when aircraft begins to take off, turbogenerator 1 is started working, compression system 5, turbogenerator firing chamber 6 and turbine 7 are arranged in the main air flow of motor, after the 5 compression superchargings of the compressed system of incoming flow air, enter turbogenerator firing chamber 6 and kerosene mixed combustion, and then, produce thrusts by 8 ejections of turbogenerator jet pipe through turbine 7 expansion actings; After aircraft reached the switching height, this moment, air pressure and density no longer were fit to turbogenerator 1 work, thereby closed turbogenerator 1, and starting solid (or liquid) rocket motor 3 is pushed into the high-altitude with aircraft; In the return course, aircraft can be done unpowered glide earlier, during to switching height and near-earth flight, can reset turbogenerator 1 again, does dynamic maneuvering flight; After aircraft returns ground,, can change rocket motor 3 and rocket motor variable area nozzle 9 easily, reach quick reusable requirement in view of the characteristics of nested structure.
Claims (3)
1. turbine-rocket embedded type engine, form by turbogenerator (1) and rocket motor (3), it is characterized in that, the axle of turbogenerator (1) is a quill shaft, the axle front end is the turbogenerator inlet cone (2) of taper, rocket motor (3) is embedded in turbogenerator inlet cone (2) and the quill shaft, and guide-ring (4) is positioned at the rear end of turbogenerator inlet cone (2); The wheel disc of compression system (5) adopts key or bearing ways of connecting to be fixed on the axle, and the tooth-like or brush seal of combing is adopted in the front and back of compression system (5); Turbine rotor (7) adopts bolt or bearing ways of connecting to be fixed on the axle, its import and export and the inboard brush seal that adopts; Turbogenerator firing chamber (6) is positioned between compression system (5) and the turbine rotor (7); The closed rocket motor variable area nozzle (9) and the external casing of turbogenerator constitute turbogenerator jet pipe (8) jointly, and support plate (10) is connected with turbogenerator inlet cone (2) by riveted joint or welding or bolt or screw or pin.
2. a kind of turbine-rocket embedded type engine as claimed in claim 1 is characterized in that, described rocket motor (3) is solid propellant rocket or liquid propellant rocket engine.
3. a kind of turbine-rocket embedded type engine as claimed in claim 1 is characterized in that, described compression system (5) is axial-flow compressor or centrifugal-flow compressor or rotary punching compression rotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200149740U CN201083164Y (en) | 2007-09-28 | 2007-09-28 | Turbine-rocket embedded type engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200149740U CN201083164Y (en) | 2007-09-28 | 2007-09-28 | Turbine-rocket embedded type engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201083164Y true CN201083164Y (en) | 2008-07-09 |
Family
ID=39625630
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2007200149740U Expired - Fee Related CN201083164Y (en) | 2007-09-28 | 2007-09-28 | Turbine-rocket embedded type engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201083164Y (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103726952A (en) * | 2012-10-11 | 2014-04-16 | 高荣江 | Divided-flow type gas turbine engine |
| CN105129096A (en) * | 2015-07-14 | 2015-12-09 | 洛阳大智实业有限公司 | Novel dual-power tandem loitering powerplant |
-
2007
- 2007-09-28 CN CNU2007200149740U patent/CN201083164Y/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103726952A (en) * | 2012-10-11 | 2014-04-16 | 高荣江 | Divided-flow type gas turbine engine |
| CN103726952B (en) * | 2012-10-11 | 2016-07-13 | 高荣江 | Shunting gas-turbine unit |
| CN105129096A (en) * | 2015-07-14 | 2015-12-09 | 洛阳大智实业有限公司 | Novel dual-power tandem loitering powerplant |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20080709 Termination date: 20130928 |