CN115263600B - Exoskeleton turbine punching combined engine and control method - Google Patents
Exoskeleton turbine punching combined engine and control method Download PDFInfo
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- CN115263600B CN115263600B CN202210812688.8A CN202210812688A CN115263600B CN 115263600 B CN115263600 B CN 115263600B CN 202210812688 A CN202210812688 A CN 202210812688A CN 115263600 B CN115263600 B CN 115263600B
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- 238000004080 punching Methods 0.000 title claims abstract description 25
- 238000000034 method Methods 0.000 title claims abstract description 10
- 238000002485 combustion reaction Methods 0.000 claims abstract description 34
- 230000006835 compression Effects 0.000 claims description 7
- 238000007906 compression Methods 0.000 claims description 7
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- 238000006243 chemical reaction Methods 0.000 abstract description 9
- 230000008901 benefit Effects 0.000 abstract description 8
- 230000010354 integration Effects 0.000 abstract description 8
- 239000000725 suspension Substances 0.000 abstract description 5
- 230000007704 transition Effects 0.000 abstract description 2
- 230000001105 regulatory effect Effects 0.000 description 9
- 238000010586 diagram Methods 0.000 description 8
- 230000033228 biological regulation Effects 0.000 description 4
- 239000000243 solution Substances 0.000 description 4
- 230000006872 improvement Effects 0.000 description 3
- 230000033001 locomotion Effects 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000003921 oil Substances 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 241000282414 Homo sapiens Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 230000005672 electromagnetic field Effects 0.000 description 1
- 230000005674 electromagnetic induction Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/16—Composite ram-jet/turbo-jet engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/15—Control or regulation
- F02K1/16—Control or regulation conjointly with another control
- F02K1/165—Control or regulation conjointly with another control with air intake control
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses an exoskeleton turbine punching combined engine and a control method, which belong to the technical field of aerospace engines, and by introducing a novel exoskeleton turbine engine configuration and a superconductive magnetic suspension hollow bearing structure integrated design concept, coaxial serial layout of a circular section punching engine in the center and an exoskeleton turbine core engine in an outer ring is adopted, an axisymmetric adjustable air inlet channel, a common super combustion chamber and an adjustable tail nozzle are shared, the space sharing degree and the structural integration level are maximized, and meanwhile, the multimode efficient thermal matching work and modal transition conversion control requirements in an extremely wide flight Mach number range are realized by a limited structure adjusting mode in the engine, the performance advantages of the turbine engine and the punching engine and the structural advantages of the exoskeleton configuration are fully exerted, the overall structure is more compact and lighter, the thrust-weight ratio is improved, and the horizontal take-off and landing repeated high-speed flight with higher efficiency and farther range can be satisfied.
Description
Technical Field
The invention belongs to the technical field of aerospace engines, and particularly relates to an exoskeleton turbine punching combined engine and a control method.
Background
The realization of faster, higher and more distant flying is the continuous pursuit of human beings on flying, the horizontal take-off and landing, and the repeatedly used remote hypersonic aircraft is the main strategic development direction of the future aviation aircraft, the flight envelope range is very wide, and the flight Mach number is extended from subsonic, transonic and supersonic to hypersonic. It is expected that the power plant will be the core of achieving hypersonic flight in the wide speed domain. Currently, the flight Mach number adapted to an aviation turbine engine is generally between Ma0 and Ma 3, and the ramjet engine does not have low-speed starting working capacity and needs to be above the flight Mach number 2, wherein the sub-combustion ramjet engine can adapt to the flight Mach numbers between Ma2 and Ma6, and the flight Mach number of the super-combustion ramjet engine can be larger than Ma6. Therefore, the traditional single-type suction power device cannot meet the propulsion requirement of the hypersonic aeroplane in the horizontal take-off and landing range. For this reason, the combination of a conventional turbine engine and a ramjet engine has been proposed, and an air-breathing type combined power device represented by a turbine-based combined cycle engine (TBCC) has evolved to meet the requirement of repeated use of hypersonic flight in horizontal take-off and landing.
The turbine-based combined cycle engine (TBCC) integrates the advantages of the turbine engine and the ramjet engine in the respective applicable flight ranges, so that the turbine-based combined cycle engine has the advantages of capability of taking off and landing at regular level, repeated use, high reliability, excellent low-speed performance (the theoretical specific impulse of the turbine engine is highest in various engines in the stage of Ma < 3), small technical risk and the like, becomes an ideal power device selection for a hypersonic military civil aircraft, a hypersonic cruise missile and a two-stage in-orbit aerospace aircraft in the future, and has good engineering application prospect. According to the relative position relation between the turbine engine and the ramjet, the TBCC engine can be divided into a coaxial layout and an up-down layout, wherein the coaxial layout can be divided into a coaxial serial type (the turbine engine and the ramjet are serially connected front and back, a stress application/ramjet shared combustion chamber is adopted) and a coaxial surrounding type (the turbine engine is positioned in the center, and a ramjet channel surrounds the outside of the turbine engine and works independently); the upper and lower parallel type layout often adopts the channel layout of which the turbine engine and the ramjet engine are respectively arranged independently, and can be divided into an outer parallel type and an inner parallel type according to different air inlet modes.
However, TBCC combined cycle engines based on conventional mature off-the-shelf turbine engines, whether in a serial or parallel arrangement, still face some critical bottleneck problems in terms of structural integration, overall performance, etc., limiting engineering applications. The main appearance is that: 1) The traditional layout mode mainly comprises the steps of carrying out structural combination integration around the turbine engine, wherein a ramjet channel is either surrounded outside the turbine engine or independently connected with the channel in parallel, so that the space sharing degree and the structural integration degree are low; 2) The engine has higher volume occupation and large structural weight (particularly a turbine engine), and the dead load influence is remarkable during high Mach number acceleration and cruising flight, so that the improvement of the combined propulsion comprehensive performance is not facilitated; 3) The wide-range multichannel air inlet channel adjustment and matching performance, modal conversion adjustment, tail nozzle adjustment and the like are greatly influenced by the restriction of a combined layout mode, and the contradiction between the engine performance and the degree of freedom of variable structure adjustment and the structure weight is prominent; 4) The real-time output/supply of the power of the engine system, the integrated design and integration are key to comprehensive optimization. Therefore, an integral and innovative solution is required to be provided for the turbine and the ramjet in the aspects of combined working mode, combined configuration layout, integrated design and integration and the like, so that the comprehensive performance of combined propulsion is improved, and hypersonic flight with higher efficiency and farther voyage is satisfied.
Disclosure of Invention
Aiming at the defects and improvement demands of the prior art, the invention provides an exoskeleton turbine punching combined engine and a control method, wherein a novel exoskeleton turbine engine is innovatively adopted, a traditional combined layout mode is overturned, a coaxial serial layout of a circular section punching engine in the center and an exoskeleton turbine core engine in the outer ring is adopted, an axisymmetric subject air inlet channel, a super combustion chamber and an adjustable tail nozzle are shared, the space sharing degree and the structural integration level are maximized, the performance advantages of the turbine engine and the punching engine and the structural advantages of an exoskeleton configuration are fully exerted, and the aim is to design a turbine punching combined engine scheme which is compact in structure, higher in integration level, lighter in weight and larger in thrust weight, meets the requirements of wide Mach number high-performance work, and supports the high-efficiency propulsion demands of a horizontal take-off and landing, repeated use and remote hypersonic aircraft.
To achieve the above object, in a first aspect, the present invention provides an exoskeleton turbine-ramjet combined engine, including: the engine comprises a central cone, an engine body shell, a split flow regulating plate, an outer skeleton turbine core machine, a ramjet engine, a shared super combustion chamber and a tail nozzle;
The tail cone of the center cone extends into the machine body shell and is fixedly connected with the machine body shell; the conical surface of the central cone and the inner wall of the machine body shell form an adjustable air inlet channel; the front cone of the center cone can move back and forth so as to realize compression and capture of air flows under different Mach numbers;
The outer framework turbine core machine is arranged in the machine body shell and comprises a fixed support plate, stator blades, rotor blades and a permanent magnet shell from inside to outside; the fixed support plate is in a circular ring shape and surrounds a stamping channel of the stamping engine; the stator blades are fixed on the fixed support plate and grow outwards; the rotor blades are fixed on the permanent magnet shell, grow inwards and are distributed with the stator blades in a staggered manner;
The split-flow adjusting plate is connected with one end of the fixed support plate, which is close to the center cone, and can rotate to adjust air flow entering the outer framework turbine core machine and the ramjet engine;
the adjustable air inlet channel, the shared super combustion chamber and the tail spray pipe are sequentially connected.
Further, the center cone comprises a front cone, a thimble, a sleeve and a tail cone; the tail cone is fixedly connected with the engine body shell through four support plates with a circumferential distance of 90 degrees, and the sleeve is fixedly connected with the tail cone; the front cone is fixedly connected with the thimble and can move back and forth along the sleeve.
Further, the exoskeleton turbine core engine further comprises a turbine combustion chamber, wherein the turbine combustion chamber is fixed on the fixed support plate and is positioned at the middle rear part of the exoskeleton turbine core engine air passage.
Further, the rotor blade is a permanent magnet.
Further, the ramjet engine further includes: and the oil injection support plate is fixed on the fixed support plate in the stamping channel.
Further, the common super combustor inlet may be moved back and forth.
Further, the nozzle throat area may be adjusted based on the drop ratio and expansion requirements.
In a second aspect, the present invention further provides a control method for the operation of the exoskeleton turbine-ramjet combined engine according to the first aspect, where the exoskeleton turbine-ramjet combined engine is applicable to a range of flight mach numbers 0-7, and Ma is a current incoming flow mach number:
When Ma is more than 0 and less than or equal to 2.0, the front cone of the center cone is positioned at the rearmost end, the flow dividing adjusting plate is contacted with the center cone, and air flow completely enters the outer framework turbine core machine;
When Ma is less than or equal to 2.0 and less than or equal to 3.0, the front cone of the center cone moves forward, the flow distribution adjusting plate changes at the middle position according to the incoming flow condition so as to meet the requirement of air flow distribution, and air flow enters the outer framework turbine core machine and the ramjet engine simultaneously;
when Ma is less than or equal to 3.0 and less than or equal to 6.0, the center cone moves forward to the front end, the split flow regulating plate is contacted with the engine body shell, and air flow completely enters the ramjet engine;
when the Ma is less than or equal to 6.0 and is less than or equal to 7.0, the center cone moves forward to the forefront end, the flow dividing adjusting plate is contacted with the engine body shell, and air flow completely enters the ramjet engine.
In general, through the above technical solutions conceived by the present invention, the following beneficial effects can be obtained:
(1) The design scheme of the coaxial serial turbine punching combined engine based on the outer skeleton turbine engine and the circular section center punching engine is innovatively provided, wherein the outstanding characteristics are the design idea of the turbine core engine with the outer skeleton structure, and rotor blades are suspended from outside to inside on a hollow bearing shell, so that heavy wheel discs, hubs and bearings in the traditional turbine engine are omitted, meanwhile, the rotor blades show inward compressive stress in the high-speed rotation process, the rigidity and the strength are better, and the structural volume and the weight of the turbine core engine are basically reduced. Meanwhile, the outer skeleton structure turbine core machine adopts a novel superconductive magnetic suspension hollow bearing structure integrated design scheme, and provides non-contact supporting force for the high-speed rotating component through the magnetic suspension effect of the permanent magnet in the electromagnetic field, so that the requirements for high-performance bearing materials in the traditional main shaft design are reduced, and the non-contact relative rotary motion can be realized, the friction loss of the traditional bearing rotary motion is eliminated, meanwhile, the requirement for a lubricating oil accessory system is greatly reduced, and the complexity and the weight of the system are reduced.
(2) Compared with the traditional serial combination layout mode, the integrated internal structure of the central hollow shell of the external skeleton turbine core machine integrates the channels of the ramjet, can realize the conversion from the traditional external annular flow channel into the central circular section flow channel configuration, shares the internal structure space to the maximum extent, simultaneously greatly reduces the wet area (contact area with air flow) of the flow channel of the ramjet, reduces the pneumatic friction resistance and the heat-proof area of the structure, and is favorable for improving the comprehensive propulsion performance of the working stage of the ramjet. In addition, through the expansion matching design of the flow passage area of the central circular section ramjet engine, the pure super-combustion mode work with the speed of more than Ma 6-7 can be realized, and the working capacity of adapting to higher flight Mach numbers is realized.
(3) Based on the integrated matching thought of an adjustable air inlet channel, a turbine core machine, a multi-mode combustion chamber and an adjustable tail nozzle, the adjustable air inlet channel mainly comprises a center cone, a split adjusting plate, a turbine core machine outlet adjusting door, a tail nozzle throat and the like in a limited structure adjusting mode in an engine, can meet the adjustment and control of a turbine mode, a turbine-stamping transition mode, a sub-combustion stamping mode and a super-combustion stamping mode, can realize the high-efficiency thermal matching work and mode conversion control requirements in an extremely wide working Mach number range through component variable structure adjustment, and better plays the full-envelope propulsion performance advantage of the turbine stamping combined engine.
Drawings
FIG. 1 is a schematic diagram of the overall structure of an exoskeleton turbine-ramjet combined engine provided by an embodiment of the present invention;
FIG. 2 is a schematic diagram of an adjustable intake passage according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of an exoskeleton turbine core machine and a ramjet engine according to an embodiment of the present invention;
FIG. 4 is a cross-sectional view of an exoskeleton turbine ramjet combined engine provided by an embodiment of the present invention;
FIG. 5 is a schematic diagram of a common super combustor and tail nozzle according to an embodiment of the present invention;
FIG. 6 is a schematic diagram of an exoskeleton turbine punching combined engine provided by an embodiment of the invention when the value of Ma is 0< 2;
FIG. 7 is a schematic diagram of the operation of the exoskeleton turbine punching combined engine provided by the embodiment of the invention when 2< Ma is less than or equal to 3;
FIG. 8 is a schematic diagram of an exoskeleton turbine punching combined engine provided by the embodiment of the invention in operation with a value of 3< Ma < 6;
FIG. 9 is a schematic diagram of an exoskeleton turbine punching combined engine provided by an embodiment of the invention operating at 6 < Ma.ltoreq.7;
The same reference numbers are used throughout the drawings to reference like elements or structures, wherein: 1-center cone, 2-engine body shell, 3-split regulating plate, 4-outer skeleton turbine core, 5-ramjet, 6-shared super combustor, 7-tail nozzle, 8-adjustable air inlet channel, 41-fixed support plate, 42-stator blade, 43-rotor blade, 44-turbine combustor, 45-turbine air inlet, 46-turbine combustion chamber outlet, 47-permanent magnet shell, 48-electromagnetic field, 51-ram channel, 52-ram channel inner oil injection support plate, 61-shared super combustor inlet, 81-air inlet lip, 82-air inlet throat, 83-low speed air inlet channel and 84-high speed air inlet channel.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention. In addition, the technical features of the embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
In the present invention, the terms "first," "second," and the like in the description and in the drawings, if any, are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order.
Referring to fig. 1, in combination with fig. 2 to 5, the present invention provides an exo-skeleton turbine-ramjet combined engine, comprising: the engine comprises a central cone 1, an engine body shell 2, a split flow regulating plate 3, an outer skeleton turbine core machine 4, a ramjet engine 5, a shared super combustion chamber 6 and a tail nozzle 7.
The center cone 1 comprises a front cone, a thimble, a sleeve and a tail cone; the tail cone of the center cone 1 extends into the machine body shell 2 and is fixedly connected with the machine body shell 2 through four support plates with a circumferential distance of 90 degrees, an adjustable air inlet channel 8 is formed between the conical surface of the center cone and the inner wall of the machine body shell 2, and the sleeve is fixedly connected with the tail cone; the front cone is fixedly connected with the thimble, can move back and forth along the sleeve, and is provided with a matched chute and a locking mechanism, on one hand, the front cone is combined with the inlet lip 81 to realize compression and capture of air flow under different Mach numbers, and meanwhile, the area of the inlet throat 82 can be changed by the movement of the center cone 1, so that the matching of flow and compression is better realized.
The outer skeleton turbine core machine 4 adopts an outer skeleton structure, so that a heavy main shaft of a traditional axisymmetric turbine engine is removed. The outer skeleton turbine core machine 4 is arranged inside the machine body shell 2 and comprises a fixed support plate 41, stator blades 42, rotor blades 43 and a permanent magnet shell 47 from inside to outside; the fixed support plate 41 is circular and surrounds a punching passage 51 of the punching engine 5; the stator blades 42 are fixed on the fixed support plate 41 and grow outwards; the rotor blades 43 are fixed to the permanent magnet housing 47 and are grown inward and staggered with respect to the stator blades 42. The permanent magnet housing 47 and the rotor blade 43 are integrally formed by permanent magnets, and when the supporting force is provided by the magnetic field and the generated current is supplied to the magnetic field and the electromagnetic geometry adjusting system, a closed loop of the circuit is formed; the stator blades 42 are fixed to the fixed support plate 41 without rotation.
Further, the outer skeleton turbine core machine 4 further comprises a turbine combustion chamber 44, and the turbine combustion chamber 44 is fixed on the fixed support plate 41 and is positioned at the middle rear part of the air passage of the outer skeleton turbine core machine 4.
The central region enclosed by the fixed support plate 41 serves as a punching passage 51 for the punching engine 5, so that a considerable space saving is achieved with respect to a conventional series arrangement.
The split-flow adjusting plate 3 is connected to one end of the fixed support plate 41 near the center cone 1, and is rotatable to adjust the air flow into the exo-skeleton turbine core machine 4 and the ramjet engine 5. Specifically, the low-speed air inlet channel 83 always works at Ma0-3.0 to ensure the working state of the exoskeleton turbine core 4, while the high-speed air inlet channel 84 starts to start after Ma2.0, and the ramjet engine 5 starts to work, so that mode conversion is finally realized. The split-flow adjusting plate 3 is used for realizing the double-channel intake flow distribution and air compression requirements under different Mach number incoming flow states, and meanwhile, the starting performance of the intake channel is ensured, so that safe and stable modal conversion is ensured.
The adjustable air inlet channel 8, the shared super combustion chamber 6 and the tail nozzle 7 are connected in sequence. The common super combustor inlet 61 is adjustable, and can be used as an afterburner when the turbine engine works alone, and can also be used as a sub-combustion ramjet combustor when the turbine ram works together, and can also be used as a super-combustion ramjet combustor when the ram engine works alone, so that the matching of an air inlet channel and the combustion chamber is realized, and the thermodynamic cycle is better. The tail pipe 7 can adjust the throat area of the tail pipe according to the drop pressure ratio and the expansion requirement, so that the expansion ratio can be adjusted in a large range, and the exhaust requirement of Ma0-7 in a wide range can be met.
In addition, the center cone 1 can change the area of the inlet throat 82 and combine with the tail pipe 7 to realize the matching work of different working Mach numbers to flow down. By judging the air inlet under different incoming flow conditions, the electromagnetic regulating system is controlled to perform rapid geometric regulation to realize large-range flexible regulation so as to meet the air flow compression and expansion requirements of the Ma0-7 wide Mach number working range.
Further, the central cone 1 and the tail nozzle 7 work together with the shared super combustor inlet 61, so that mode conversion is better realized, the opening and closing of the channel are realized through geometric adjustment, and the aerodynamic thermal adjustment in a wide Mach number range is realized.
On the other hand, the invention also provides a control method of the exoskeleton turbine punching combined engine, wherein the Mach number working range of the exoskeleton turbine punching combined engine is 0-7, and Ma is the current incoming flow Mach number. With reference to fig. 6 to 9, the working process of the exoskeleton turbine punching combined engine provided by the invention is as follows under different mach numbers:
When Ma is 0< 2.0, the working mode is a pure turbine mode, the air flow speed is low, the front cone of the center cone 1 is positioned at a rear position, the split flow regulating plate 3 is in contact with the center cone 1, the high-speed air inlet channel 84 is closed, the low-speed air inlet channel 83 is completely opened, and the air flow enters the exoskeleton turbine core 4 completely after being compressed by shock waves and moves backwards through the shared super combustor inlet 61. The flow of air through the turbine combustor 44 enters the common super combustor 6 entirely, which is then equivalent to the afterburner of a conventional turbine engine. Meanwhile, because the air flow of the common super combustor 6 is subsonic, the tail nozzle 7 is a Laval nozzle, and firstly, the tail nozzle is contracted to Ma=1 at the throat part of the tail nozzle, and then expansion and acceleration are carried out, so that the expansion requirement at the moment is met.
And (II) when the Ma is 2.0< and less than or equal to 3.0, the working mode is that the turbine and the ramjet work together, and the turbine mode is gradually converted into the ramjet mode along with the increase of the flight Mach number. As the Mach number of the incoming flow rises, the front cone of the central cone 1 moves forwards along the sleeve and is locked, so that the better compressed air can be captured better, the area of the throat 82 of the air inlet channel is increased accordingly, the split regulating plate 3 is changed at the middle position according to the incoming flow condition so as to meet the requirement of air flow distribution at any time, the low-speed air inlet channel 83 and the high-speed air inlet channel 84 are simultaneously in an open state, the air flow simultaneously enters the two channels, the exoskeleton turbine core 4 and the ramjet engine 5 work together, and finally all the air flows are converged into the common super combustion chamber 6. At this point, the common super combustor 6 air flow is still subsonic, and thus the tail nozzle 7 is still a Laval nozzle. With the mach number rising, the low speed intake passage 83 eventually closes, the common super combustor inlet 61 moves forward, closing the turbine core combustor outlet 46, and completing the turbine to ram mode conversion.
And (III) when the Ma is 3.0< and less than or equal to 6.0, the working mode is a pure stamping working mode, and the stamping engine is in a sub-combustion mode. With the gradual increase of the flight Mach number, the front cone of the center cone 1 moves forward to the front end and locks up so as to meet the air flow compression and capture requirements at the moment. At this time, all the captured air flows enter the common super combustor 6 for tissue combustion, and the air flows in the common super combustor 6 are in subsonic combustion, so that the tail nozzle 7 still adopts a Laval nozzle, a geometric throat exists, and the throat area can be adjusted in real time along with the flight Mach number and the working condition change so as to meet the requirements of throttling and exhaust.
And fourthly, when Ma is more than 6.0 and less than or equal to 7.0, the working mode is still a pure stamping working mode, but the stamping engine is in a scramjet stamping mode. At this time, the Mach number of the incoming flow is at the maximum value in the design, and the front cone of the center cone 11 moves forward to the forefront end and locks to meet the air intake requirement at this time. In the scramjet mode, the combustion zone is advanced and combustion takes place in the entire jet path 51, the gas flow taking part in combustion at supersonic speed. The expansion type spray pipe is adopted, at the moment, a geometric throat is not formed, and the burnt supersonic airflow is accelerated to expand so as to meet the exhaust requirement at the moment.
In summary, 1) the novel axisymmetric outer skeleton magnetic suspension turbine engine is introduced, so that a heavy main shaft of the traditional turbine engine is removed, the outer skeleton is supported by a magnetic suspension effect, the problem caused by insufficient bearing capacity of a bearing is avoided, the weight is greatly reduced, the compressive stress is generated by the blades growing inwards, the strength of materials is greatly enhanced, and the service life is prolonged; 2) The cavity space at the center of the fixed support plate is combined with the ramjet, so that the defect that a stamping channel is positioned on the side surface in the conventional serial TBCC arrangement is overcome, the stamping channel is enlarged, and the capturing of the incoming flow of the ramjet can be better realized under the condition of high Mach number incoming flow. The common super combustion chamber and the adjustable tail nozzle are used, so that the space is reasonably utilized, the thermodynamic cycle is optimized, and the thrust-weight ratio of the engine is greatly improved; 3) The adjustable symmetrical split flow regulating plate and the baffle in the stamping channel and the adjustable common super combustor inlet jointly act to realize large-amplitude air intake regulation, remarkably improve the air intake capturing efficiency of the engine, and simultaneously can perform modal conversion in flight to realize wide-range and multi-modal collaborative matching high-efficiency combustion; the electromagnetic induction (electromagnetic geometry regulating system) is applied to the regulation of multiple geometric structures in the runner, and the speed is high, the range is large, and the weight is light.
The invention can provide a combined power solution for the future aircrafts with larger load and longer flying distance, realize the horizontal take-off, subsonic or supersonic economical cruising, high-thrust accelerating climbing and high Mach number air suction type cruising of the aircrafts, and meet the application requirements of economy, flexibility and free convenience.
It will be readily appreciated by those skilled in the art that the foregoing description is merely a preferred embodiment of the invention and is not intended to limit the invention, but any modifications, equivalents, improvements or alternatives falling within the spirit and principles of the invention are intended to be included within the scope of the invention.
Claims (8)
1. An exoskeleton turbine ramjet combined engine, comprising: the engine comprises a central cone (1), an engine body shell (2), a diversion adjusting plate (3), an outer skeleton turbine core machine (4), a ramjet engine (5), a shared super combustion chamber (6) and a tail nozzle (7);
The tail cone of the center cone (1) extends into the machine body shell (2) and is fixedly connected with the machine body shell (2); the conical surface of the central cone (1) and the inner wall of the machine body shell (2) form an adjustable air inlet channel (8); the front cone of the center cone (1) can move back and forth so as to realize compression and capture of air flows under different Mach numbers;
The outer skeleton turbine core machine (4) is arranged in the machine body shell (2) and comprises a fixed support plate (41), stator blades (42), rotor blades (43) and a permanent magnet shell (47) from inside to outside; the fixed support plate (41) is in a circular ring shape and surrounds a punching channel (51) of the punching engine (5); the stator blades (42) are fixed on the fixed support plate (41) and grow outwards; the rotor blades (43) are fixed on the permanent magnet shell (47) and grow inwards and are distributed in a staggered manner with the stator blades (42);
the split-flow adjusting plate (3) is connected with one end, close to the center cone (1), of the fixed support plate (41) and can rotate to adjust air flow entering the outer framework turbine core machine (4) and the ramjet engine (5);
The adjustable air inlet channel (8), the shared super combustion chamber (6) and the tail jet pipe (7) are sequentially connected.
2. The exoskeleton turbine ramjet combined engine of claim 1 wherein said center cone (1) comprises a front cone, a thimble, a sleeve and a tail cone; the tail cone is fixedly connected with the engine body shell (2) through four support plates with a circumferential distance of 90 degrees, and the sleeve is fixedly connected with the tail cone; the front cone is fixedly connected with the thimble and can move back and forth along the sleeve.
3. The exo-skeleton turbine ramjet combined engine according to claim 1 or 2, wherein the exo-skeleton turbine core machine (4) further comprises a turbine combustion chamber (44), the turbine combustion chamber (44) is fixed on a fixed support plate (41) and is located at the middle and rear part of the air passage of the exo-skeleton turbine core machine (4).
4. The exo-skeleton turbine ramjet combined engine according to claim 1 or 2, characterized in that the rotor blades (43) are permanent magnets.
5. The exo-skeleton turbine ramjet combined engine according to claim 1 or 2, wherein the ramjet engine (5) further comprises: and the oil injection support plate (52) is fixed on the fixed support plate (41) in the stamping channel.
6. The exo-skeleton turbine ramjet combined engine according to claim 1 or 2, characterized in that the common super-combustor (6) inlet is movable back and forth.
7. The exo-skeleton turbine ramjet combined engine according to claim 1 or 2, characterized in that the tail pipe (7) is capable of adjusting the tail pipe throat area according to the drop ratio and expansion demand.
8. A control method of an exo-skeleton turbo ramjet combined engine according to any one of claims 1 to 7, wherein the exo-skeleton turbo ramjet combined engine has a mach number operating range of 0-7, ma being a current incoming flow mach number;
when Ma is more than 0 and less than or equal to 2.0, the front cone of the center cone (1) is positioned at the rearmost end, the flow dividing adjusting plate (3) is contacted with the center cone (1), and air flow completely enters the outer skeleton turbine core machine (4);
When 2.0< Ma is less than or equal to 3.0, the front cone of the center cone (1) moves forwards, the flow distribution adjusting plate (3) changes at the middle position according to the incoming flow condition so as to meet the requirement of air flow distribution, and the air flow simultaneously enters the outer skeleton turbine core machine (4) and the ramjet engine (5);
When Ma is less than or equal to 3.0 and less than or equal to 6.0, the center cone (1) moves forward to the front end, the diversion adjusting plate (3) is contacted with the engine body shell (2), and air flow completely enters the ramjet engine (5);
When the Ma is 6.0< and is less than or equal to 7.0, the center cone (1) moves forward to the forefront end, the diversion adjusting plate (3) is contacted with the engine body shell (2), and the air flow completely enters the ramjet engine (5).
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| CN109538377A (en) * | 2018-11-15 | 2019-03-29 | 厦门大学 | Share three power combination engine design methods of sub- combustion combustion chamber |
| CN112228246A (en) * | 2020-10-30 | 2021-01-15 | 华中科技大学 | Rocket-based detonation and stamping combined cycle engine and use method and application thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US3172253A (en) * | 1959-01-02 | 1965-03-09 | Garrett Corp | Combination turbo and ramjet propulsion apparatus |
| EP3189226A1 (en) * | 2014-09-02 | 2017-07-12 | Titano S.R.L. | Turbocharged engine fed by magnetized fluids and associated method |
| CN114439646B (en) * | 2022-01-27 | 2022-12-06 | 西北工业大学 | Air turbine rocket stamping combined propulsion system |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109538377A (en) * | 2018-11-15 | 2019-03-29 | 厦门大学 | Share three power combination engine design methods of sub- combustion combustion chamber |
| CN112228246A (en) * | 2020-10-30 | 2021-01-15 | 华中科技大学 | Rocket-based detonation and stamping combined cycle engine and use method and application thereof |
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