CN205047319U - Draw and penetrate auxiliary type turbine punching press combination cycle dynamo - Google Patents
Draw and penetrate auxiliary type turbine punching press combination cycle dynamo Download PDFInfo
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- CN205047319U CN205047319U CN201520765238.3U CN201520765238U CN205047319U CN 205047319 U CN205047319 U CN 205047319U CN 201520765238 U CN201520765238 U CN 201520765238U CN 205047319 U CN205047319 U CN 205047319U
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- 238000004080 punching Methods 0.000 title abstract description 15
- 230000008676 import Effects 0.000 claims abstract description 10
- 238000002347 injection Methods 0.000 claims description 18
- 239000007924 injection Substances 0.000 claims description 18
- 235000011780 Diplotaxis muralis Nutrition 0.000 claims description 13
- 241001049062 Diplotaxis siifolia Species 0.000 claims description 13
- 238000010304 firing Methods 0.000 claims description 7
- 239000007789 gas Substances 0.000 abstract description 8
- 239000007921 spray Substances 0.000 abstract description 5
- 239000000567 combustion gas Substances 0.000 abstract description 4
- 230000007704 transition Effects 0.000 abstract description 4
- 230000002902 bimodal effect Effects 0.000 abstract description 2
- 238000006243 chemical reaction Methods 0.000 abstract description 2
- 230000001276 controlling effect Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 108091053398 TRIM/RBCC family Proteins 0.000 description 3
- 102000011408 Tripartite Motif Proteins Human genes 0.000 description 3
- 102100040255 Tubulin-specific chaperone C Human genes 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 3
- 108010093459 tubulin-specific chaperone C Proteins 0.000 description 3
- 239000000446 fuel Substances 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- 239000002243 precursor Substances 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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Abstract
The utility model provides a draw and penetrate auxiliary type turbine punching press combination cycle dynamo, relates to a combination cycle dynamo who is applied to the repeatedly usable of aerospace aircraft. This engine mainly by turbine engine, draw that penetrate the rocket and bimodal punching press engine constitutes. Turbine engine and punching press engine parallel operation draw and penetrate rocket and the integrated design of punching press engine. When engine from turbine engine mode during to punching press engine mode conversion, draw and penetrate the combustion -gas stream and spray from the extension board or from punching press engine lateral wall and get into the punching press engine, punching press engine import air fires air flow mixed and after burning with drawing to penetrate. Draw and penetrate the gas of rocket spun can to compensate turbine engine not enough to the thrust of punching press engine transit time, make the utility model discloses has the advantage that combined engine changes the level smooth transition.
Description
Technical field
The utility model patent relates to a kind of novel compositions motor, in particular to a kind of reusable injection auxiliary type turboram combination circulation (Ejector-AssistantTurbine-BasedCombinedCycle is called for short E-TBCC) motor being applied to aerospace flight vehicle.
Background technique
Combined engine is the important development direction of following empty sky one armament systems, will be also the major impetus form of aerospace flight vehicle of future generation.At present, combined engine comprises turbine base combined cycle engine (TurbineBasedCombinedCycle, hereinafter referred to as TBCC) and the large class of rocket based combined cycle motor (RocketBasedCombinedCycle, hereinafter referred to as RBCC) two.The airbreathing motor that TBCC power system is organically combined by turbojet (or turbofan) motor and pressed engine; Rocket and dual-mode scramjet are organically combined the combination circulatory system formed by RBCC.Along with going deep into combined cycle engine research work, the problem run into gets more and more, and technical difficulty is increasing.
The subject matter of RBCC motor is high at rocket stage oil consumption rate, and because needs carry oxygenant, takeoff phase, the quality of aircraft was maximum, can account for about 30% of whole oil mass from takeoff phase to the punching press stage.The subject matter of TBCC motor turns grade transition temperature at turbine to punching press to exist not steady.Above shortcoming causes the development of two class combined engines all to there is bottleneck problem.
Model utility content
The purpose of this utility model is less for specific impulse in current rocket punching press combination, and in turboram combination, there is the bottleneck problem that cannot turn level, a kind of injection auxiliary type turboram combined cycle engine is provided, namely turbine replacement rocket booster is adopted to overcome the oil consumption rate that takes off large, injection burning is adopted to overcome the inefficient difficult problem of Ma2-3 pressed engine, therefore can make full use of each motor advantage, the difficulty turning level between current all kinds of motor can be solved again.
For achieving the above object, the technical solution of the utility model is as follows:
A kind of injection auxiliary type turboram combined cycle engine, this combined cycle engine comprises turbogenerator and Dual-mode Scramjet; Turbogenerator contains turbogenerator intake duct, gas compressor, firing chamber, turbine, tail pipe burner and turbogenerator jet pipe; Dual-mode Scramjet contains ramjet engine air inlet, pressed engine distance piece, scramjet combustor and pressed engine jet pipe; Described Dual-mode Scramjet is arranged on the below of turbogenerator with parallel way; It is characterized in that: the wall Rocket ejector that described combined cycle engine is also arranged in juxtaposition containing multiple, multiple groove of being arranged in juxtaposition and switch controlling device; Multiple grooves be arranged in juxtaposition are positioned at the lower wall surface of pressed engine distance piece passage, and each wall Rocket ejector correspondence is arranged on the sidewall step front of a groove; Described switching controlling device comprises turbogenerator import fender plate, turbogenerator outlet fender plate, pressed engine is adjustable leading edge and the adjustable trailing edge of pressed engine.
A kind of injection auxiliary type turboram combined cycle engine, this combined cycle engine comprises turbogenerator and Dual-mode Scramjet; Turbogenerator contains turbogenerator intake duct, gas compressor, firing chamber, turbine, tail pipe burner and turbogenerator jet pipe; Dual-mode Scramjet contains ramjet engine air inlet, pressed engine distance piece, scramjet combustor and pressed engine jet pipe; Described Dual-mode Scramjet is arranged on the below of turbogenerator with parallel way; It is characterized in that: the support plate Rocket ejector that described combined cycle engine is also arranged in juxtaposition containing multiple, multiple support plate of being arranged in juxtaposition and switch controlling device; Multiple support plate be arranged in juxtaposition is fixed on the lower wall surface in scramjet combustor passage, and each support plate Rocket ejector correspondence is arranged on the trailing edge front of a support plate; Described switching controlling device comprises turbogenerator import fender plate, turbogenerator outlet fender plate, pressed engine is adjustable leading edge and the adjustable trailing edge of pressed engine.
In technique scheme, turbogenerator adopts turbojet engine or turbofan engine.
The utility model compared with prior art, to have the following advantages and high-lighting effect: it is not enough to thrust during pressed engine transition that the combustion gas of Rocket ejector ejection can make up turbine, the utility model is had advantage that combined engine turns grade smooth transition; In addition, the utility model, by Rocket ejector and pressed engine integrated design, can make full use of all kinds of motor advantage, has than rocket punching press combination than the advantage of leaping high.
Accompanying drawing explanation
Fig. 1 is wall injection auxiliary type turboram combination circulation (E-TBCC) engine structure schematic diagram.
Fig. 2 is the layout schematic diagram of wall Rocket ejector in passage.
Fig. 3 is support plate injection auxiliary type turboram combination circulation (E-TBCC) engine structure schematic diagram.
Fig. 4 is the layout schematic diagram of support plate Rocket ejector in passage.
In figure: 1-aircraft precursor; 2-turbogenerator intake duct; 3-aircraft fuselage; 4-turbogenerator inlet cone; 5-water conservancy diversion support plate; 6-gas compressor; 7-turbogenerator; 8-firing chamber; 9-turbine; 10-tail pipe burner; 11-turbogenerator jet pipe; Body after 12-aircraft; 13-turbogenerator outlet fender plate; 14-pressed engine jet pipe; 15-pressed engine is adjustable trailing edge; 16-Dual-mode Scramjet; 17-scramjet combustor; 18-groove; 19-wall Rocket ejector; 20-pressed engine distance piece; 21-ramjet engine air inlet; Leading edge that 22-pressed engine is adjustable; 23-turbogenerator import fender plate; 24-support plate Rocket ejector; Spray-hole after 25-support plate; 26-support plate; Spray-hole before 27-support plate
Embodiment
Below in conjunction with accompanying drawing, structure of the present utility model, principle and working procedure are described in detail.
As shown in Figure 1 to 4, injection auxiliary type turboram combined cycle engine (E-TBCC motor) of the present utility model is based on the motor basis integrated with aircraft, by wall Rocket ejector 19 or support plate Rocket ejector 24 integrated with Dual-mode Scramjet 16, adopt the mode of wall injection or support plate injection to solve turbogenerator pattern to what face during pressed engine patten transformation and push away hypodynamic problem.This combined cycle engine is primarily of turbogenerator (turbojet engine or turbofan engine) 7, Dual-mode Scramjet 16, multiple wall Rocket ejector 19 of being arranged in juxtaposition and multiple groove (or multiple support plate Rocket ejector of being arranged in juxtaposition and multiple support plate be arranged in juxtaposition) be arranged in juxtaposition; Multiple grooves be arranged in juxtaposition are positioned at the lower wall surface of pressed engine distance piece passage, and each wall Rocket ejector correspondence is arranged on the sidewall step front of a groove, and multiple wall Rocket ejector 19 sprays at each self-corresponding groove 18 sidewall step place respectively.According to support plate Rocket ejector and support plate, then multiple support plate be arranged in juxtaposition is fixed on the lower wall surface in scramjet combustor passage, each support plate Rocket ejector correspondence is arranged on the trailing edge front of a support plate, and multiple support plate Rocket ejector 24 sprays at each self-corresponding support plate 26 trailing edge respectively.
Turboramjet engine 7 is made up of turbogenerator intake duct 2, gas compressor 6, firing chamber 8, turbine 9, tail pipe burner 10 and turbogenerator jet pipe 11, be arranged on the bottom of aircraft fuselage 3, after turbogenerator inlet cone 4, water conservancy diversion support plate 5 is by welding or rivet or being threadedly connected to aircraft fuselage 3, and is connected with Dual-mode Scramjet 16 upper wall surface.Dual-mode Scramjet 16 is arranged on below turbogenerator 7, is made up of ramjet engine air inlet 21, pressed engine distance piece 20, scramjet combustor 17 and pressed engine jet pipe 14; Injection gas stream enters pressed engine from pressed engine groove 18 sidewall or from the injection of support plate 26 trailing edge, and pressed engine inlet air mixes with injection gas stream and afterburning.Aircraft machine precursor 1 lower surface, turbogenerator intake duct 2, ramjet engine air inlet 21, turbogenerator import fender plate 23 and the adjustable leading edge 22 of pressed engine form the intake duct of combined engine; After aircraft, body 12 lower surface, turbogenerator jet pipe 11, pressed engine jet pipe 14 and turbogenerator export fender plate 13, pressed engine is adjustable, and trailing edge 15 forms the jet pipe of combined engine.The conversion of the operation mode of motor realizes by regulating switching controlling device.
Wall Rocket ejector 19 and support plate Rocket ejector 24 arrangement in runner respectively as shown in Figure 2 and Figure 4, for wall Rocket ejector 19, it is arranged on the sidewall step front of groove 18, its further groove 18 is positioned at the lower wall surface of pressed engine distance piece 20 passage, multiple wall Rocket ejector 19 is evenly arranged in parallel in dual-mode scramjet 16 passage, and sprays at each self-corresponding groove 18 sidewall step place respectively; For support plate Rocket ejector 24, it is arranged on the trailing edge front of support plate 26, wherein support plate 26 is fixed on the lower wall surface in scramjet combustor 17 passage, multiple support plate Rocket ejector is evenly arranged in parallel in Dual-mode Scramjet 16 passage, and sprays at each self-corresponding support plate 26 trailing edge respectively.
The working procedure of E-TBCC motor of the present utility model is: when aircraft takes off from ground, turbogenerator import fender plate 23 is in straight position, leading edge 22 that pressed engine is adjustable and the adjustable trailing edge 15 of pressed engine are inclined upwardly, export fender plate 13 with turbogenerator import fender plate 23 and turbogenerator respectively to overlap, air-flow enters deceleration supercharging from turbogenerator intake duct 2, turbogenerator 7 starts work, air is after gas compressor 6 supercharging, burn with fuel blending in firing chamber 8, combustion gas is expanded through turbine 9, and after tail pipe burner 10 afterburning, thrust is produced in jet pipe 11, when turbogenerator 7 works after Mach number 2, by regulating turbogenerator import fender plate 23, close turbogenerator intake duct 2 gradually, meanwhile regulate the adjustable leading edge 22 of pressed engine, Rocket ejector 19 or 24 ignition trigger, fuel-rich combustion gas is ejected in pressed engine wall Rocket ejector 19 or support plate Rocket ejector 24, with the blending of ramjet engine air inlet 21 leaked-in air, and burn further.Injection pattern co-operation now in turbogenerator 7 and pressed engine 16, turbogenerator intake duct 2 area progressively reduces, and ramjet engine air inlet 21 area progressively increases, when flight Mach number is increased to 3, close turbogenerator intake duct 2, ramjet engine air inlet 21 is all opened, simultaneously, Dual-mode Scramjet 16 starting ignition, bimodal ultra-combustion ramjet pressed engine 16 and Rocket ejector 19 or 24 co-operation, when Mach number is increased to 4, close Rocket ejector 19 or 24, Dual-mode Scramjet 16 enters sub-combustion punching press mode, when Mach number is increased to 6, Dual-mode Scramjet 16 enters ultra-combustion ramjet mode.
Claims (3)
1. an injection auxiliary type turboram combined cycle engine, this combined cycle engine comprises turbogenerator (7) and Dual-mode Scramjet (16); Turbogenerator (7) is containing turbogenerator intake duct (2), gas compressor (6), firing chamber (8), turbine (9), tail pipe burner (10) and turbogenerator jet pipe (11); Dual-mode Scramjet (16) is containing ramjet engine air inlet (21), pressed engine distance piece (20), scramjet combustor (17) and pressed engine jet pipe (14); Described Dual-mode Scramjet (16) is arranged on the below of turbogenerator (7) with parallel way; It is characterized in that: the wall Rocket ejector (19) that described combined cycle engine is also arranged in juxtaposition containing multiple, multiple groove (18) of being arranged in juxtaposition and switching controlling device; Multiple grooves (18) be arranged in juxtaposition are positioned at the lower wall surface of pressed engine distance piece (20) passage, and each wall Rocket ejector (19) correspondence is arranged on the sidewall step front of a groove (18); Described switching controlling device comprises turbogenerator import fender plate (23), turbogenerator outlet fender plate (13), pressed engine is adjustable leading edge (22) and the adjustable trailing edge of pressed engine (15).
2. an injection auxiliary type turboram combined cycle engine, this combined cycle engine comprises turbogenerator (7) and Dual-mode Scramjet (16); Turbogenerator (7) is containing turbogenerator intake duct (2), gas compressor (6), firing chamber (8), turbine (9), tail pipe burner (10) and turbogenerator jet pipe (11); Dual-mode Scramjet (16) is containing ramjet engine air inlet (21), pressed engine distance piece (20), scramjet combustor (17) and pressed engine jet pipe (14); Described Dual-mode Scramjet (16) is arranged on the below of turbogenerator (7) with parallel way; It is characterized in that: the support plate Rocket ejector (24) that described combined cycle engine is also arranged in juxtaposition containing multiple, multiple support plate (26) of being arranged in juxtaposition and switching controlling device; Multiple support plate be arranged in juxtaposition is fixed on the lower wall surface in scramjet combustor (17) passage, and each support plate Rocket ejector (24) correspondence is arranged on the trailing edge front of a support plate (26); Described switching controlling device comprises turbogenerator import fender plate (23), turbogenerator outlet fender plate (13), pressed engine is adjustable leading edge (22) and the adjustable trailing edge of pressed engine (15).
3. according to the injection auxiliary type turboram combined cycle engine described in claim 1 or 2, it is characterized in that: turbogenerator (7) adopts turbojet engine or turbofan engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520765238.3U CN205047319U (en) | 2015-09-29 | 2015-09-29 | Draw and penetrate auxiliary type turbine punching press combination cycle dynamo |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520765238.3U CN205047319U (en) | 2015-09-29 | 2015-09-29 | Draw and penetrate auxiliary type turbine punching press combination cycle dynamo |
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| CN205047319U true CN205047319U (en) | 2016-02-24 |
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| CN201520765238.3U Active CN205047319U (en) | 2015-09-29 | 2015-09-29 | Draw and penetrate auxiliary type turbine punching press combination cycle dynamo |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105156228A (en) * | 2015-09-29 | 2015-12-16 | 清华大学 | Ejector-assistant turbine-based combined cycle engine |
| CN106050472A (en) * | 2016-07-08 | 2016-10-26 | 西北工业大学 | Turbo-rocket combined ramjet engine and operating method thereof |
| CN106870162A (en) * | 2017-03-14 | 2017-06-20 | 湖北航天技术研究院总体设计所 | A kind of integrated ducted rocket air intake port blanking cover |
| CN111664022A (en) * | 2020-06-16 | 2020-09-15 | 中国人民解放军国防科技大学 | Combustion chamber of rotary detonation ramjet engine with fuel injection |
| CN112483275A (en) * | 2020-11-05 | 2021-03-12 | 邓云娣 | Propeller and aircraft |
-
2015
- 2015-09-29 CN CN201520765238.3U patent/CN205047319U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105156228A (en) * | 2015-09-29 | 2015-12-16 | 清华大学 | Ejector-assistant turbine-based combined cycle engine |
| CN106050472A (en) * | 2016-07-08 | 2016-10-26 | 西北工业大学 | Turbo-rocket combined ramjet engine and operating method thereof |
| CN106870162A (en) * | 2017-03-14 | 2017-06-20 | 湖北航天技术研究院总体设计所 | A kind of integrated ducted rocket air intake port blanking cover |
| CN111664022A (en) * | 2020-06-16 | 2020-09-15 | 中国人民解放军国防科技大学 | Combustion chamber of rotary detonation ramjet engine with fuel injection |
| CN111664022B (en) * | 2020-06-16 | 2021-06-18 | 中国人民解放军国防科技大学 | Combustion chamber of rotary detonation ramjet engine with fuel injection |
| CN112483275A (en) * | 2020-11-05 | 2021-03-12 | 邓云娣 | Propeller and aircraft |
| CN112483275B (en) * | 2020-11-05 | 2021-12-17 | 邓云娣 | Propeller and aircraft |
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