CN110107426A - Across the medium flight device power device shared based on combustion chamber between grade and turbine water sky - Google Patents

Across the medium flight device power device shared based on combustion chamber between grade and turbine water sky Download PDF

Info

Publication number
CN110107426A
CN110107426A CN201910379186.9A CN201910379186A CN110107426A CN 110107426 A CN110107426 A CN 110107426A CN 201910379186 A CN201910379186 A CN 201910379186A CN 110107426 A CN110107426 A CN 110107426A
Authority
CN
China
Prior art keywords
propulsion system
jet propulsion
pressure turbine
low
medium
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.)
Granted
Application number
CN201910379186.9A
Other languages
Chinese (zh)
Other versions
CN110107426B (en
Inventor
邵冬
张亚华
张启军
贾志刚
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
China Aero Engine Research Institute
Original Assignee
China Aero Engine Research Institute
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by China Aero Engine Research Institute filed Critical China Aero Engine Research Institute
Priority to CN201910379186.9A priority Critical patent/CN110107426B/en
Publication of CN110107426A publication Critical patent/CN110107426A/en
Application granted granted Critical
Publication of CN110107426B publication Critical patent/CN110107426B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B60VEHICLES IN GENERAL
    • B60FVEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
    • B60F5/00Other convertible vehicles, i.e. vehicles capable of travelling in or on different media
    • B60F5/02Other convertible vehicles, i.e. vehicles capable of travelling in or on different media convertible into aircraft
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B63SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63HMARINE PROPULSION OR STEERING
    • B63H11/00Marine propulsion by water jets
    • B63H11/02Marine propulsion by water jets the propulsive medium being ambient water
    • B63H11/04Marine propulsion by water jets the propulsive medium being ambient water by means of pumps
    • B63H11/06Marine propulsion by water jets the propulsive medium being ambient water by means of pumps of reciprocating type
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02Aircraft characterised by the type or position of power plants
    • B64D27/16Aircraft characterised by the type or position of power plants of jet type
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/20Adaptations of gas-turbine plants for driving vehicles
    • F02C6/203Adaptations of gas-turbine plants for driving vehicles the vehicles being waterborne vessels
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/20Adaptations of gas-turbine plants for driving vehicles
    • F02C6/206Adaptations of gas-turbine plants for driving vehicles the vehicles being airscrew driven
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, 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
    • F02C7/36Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16Control of working fluid flow
    • F02C9/18Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16Control of working fluid flow
    • F02C9/20Control of working fluid flow by throttling; by adjusting vanes
    • F02C9/22Control of working fluid flow by throttling; by adjusting vanes by adjusting turbine vanes
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26Control of fuel supply
    • F02C9/40Control of fuel supply specially adapted to the use of a special fuel or a plurality of fuels
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K3/00Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Ocean & Marine Engineering (AREA)
  • Transportation (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Jet Pumps And Other Pumps (AREA)

Abstract

Present disclose provides a kind of across medium flight device power devices shared based on combustion chamber between grade and turbine water sky comprising fanjet jet propulsion system provides power to across medium flight device when being used for flight in the sky;Pump spray hydro-jet propulsion system, provides power to across medium flight device when for submariner under water;And combustion chamber and low-pressure turbine between grade, it is shared by fanjet jet propulsion system and pump spray hydro-jet propulsion system.

Description

Across the medium flight device power device shared based on combustion chamber between grade and turbine water sky
Technical field
The disclosure belongs to aircraft power plant technical field, is related to a kind of across medium flight device power device, more particularly to A kind of across medium flight device power device shared based on combustion chamber between grade and turbine water sky.
Background technique
Across medium flight device is one of emphasis direction of following flight device development, it can be achieved that airflight and underwater submariner, A kind of novel mode of operation can be opened up.Since 20~thirties of 20th century, various countries military specialist proposes diving aircraft successively Or the imagination about across medium flight device equipment platform such as flight submarine.2008, U.S. national defense advanced research projects agency (DARPA) a kind of mixing flying platform is proposed, it is intended to merge the speed and voyage of aircraft, the function of cruising of surface ship, and The stealth capabilities of submarine.Russian Defence Ministry then started the underwater unmanned plane authorization exploitation carried by submarine in 2015.But It is to be limited by technical level, is converted into type of project not successfully.
It is to meet the requirement to work under water, empty two media environment across medium engine, is that support development flies across medium The key of boat device.However, aerial power and underwater engine differ from one another in working principle with working method, differ greatly, and knot The totally different more difficult unification of structure;Current power system mostly uses greatly the form of the two simple combination, and aerial power generally uses aviation to fire Gas eddy turbine and piston engine, underwater engine is using motor driven or heat power driving water paddle or pump leaf, drawback body The aspects such as level of integrated system is poor, structure is not compact, deadweight is big, propulsive efficiency is low now.
In order to guarantee normal work of across the medium flight device under different operating environment, across medium power device must consider more The factor of aspect: structure design will rationally, and mitigation weight as far as possible reduces space;Efficiency with higher, high-speed flight ability and Preferable Project Realization, however there is larger limitation in these areas in the prior art.
Summary of the invention
In order to solve at least one above-mentioned technical problem, it is empty based on combustion chamber between grade and turbine water that present disclose provides one kind Shared across medium flight device power device comprising fanjet jet propulsion system, be used for flight in the sky when to across Medium flight device provides power;Pump spray hydro-jet propulsion system, provides power to across medium flight device when for submariner under water;With And combustion chamber and low-pressure turbine between grade, it is shared by fanjet jet propulsion system and pump spray hydro-jet propulsion system.
According at least one embodiment of the disclosure, across medium flight device power device further includes clutch and mode choosing Valve is selected, for realizing the conversion of fanjet jet propulsion system and pump spray hydro-jet propulsion system.
According at least one embodiment of the disclosure, when fanjet jet propulsion system works, low-pressure turbine is logical It crosses clutch to connect with fanjet jet propulsion system, model selection valve is in the open state, so that flowing before low-pressure turbine Road connection;And when pump spray hydro-jet propulsion system work, low-pressure turbine is connect by clutch with pump spray hydro-jet propulsion system, mould Formula selector valve is in close state, so that flow path seals before low-pressure turbine.
According at least one embodiment of the disclosure, fanjet jet propulsion system includes fan, for sucking Air generates compressed air;High-pressure compressor is used for compressed air, generates high pressure air;Main chamber, in main burning Room high pressure air is mixed with fuel, and ignition, generates combustion gas;And high-pressure turbine, it is pushed by combustion gas, while high pressure Turbine is for driving high-pressure compressor.
According at least one embodiment of the disclosure, when fanjet jet propulsion system works, low-pressure turbine is logical It crosses clutch to connect with fan, combustion gas pushes low-pressure turbine rotation, and low-pressure turbine is used for driving fan.
According at least one embodiment of the disclosure, when fanjet jet propulsion system works, combustion chamber between grade Fuel be aviation kerosine, combustion chamber is used to provide extra-push model to across medium flight device between grade.
According at least one embodiment of the disclosure, pump spray hydro-jet propulsion system includes power output shaft, transmission mechanism With pump leaf;Wherein, one end of power output shaft and transmission mechanism connects;And the other end connection of pump leaf and transmission mechanism, pump Leaf is used for the aqueous medium for accelerating to suck from water inlet.
According at least one embodiment of the disclosure, when pump spray hydro-jet propulsion system works, low-pressure turbine passes through clutch Device and power output axis connection.
According at least one embodiment of the disclosure, when pump spray hydro-jet propulsion system works, the fuel of combustion chamber between grade For propellant needed for underwater operation, propellant combustion chambers burn between grade generates combustion gas, and combustion gas pushes low-pressure turbine, low pressure Turbine drives power output shaft, power output shaft pass through transmission mechanism transfer tube leaf.
According at least one embodiment of the disclosure, across medium flight device power device further includes the adjustable machine of Turbomachinery Structure, for adjusting stator blade established angle, to meet the work of fanjet jet propulsion system and pump spray hydro-jet propulsion system respectively It is required.
Detailed description of the invention
Attached drawing shows the illustrative embodiments of the disclosure, and it is bright together for explaining the principles of this disclosure, Which includes these attached drawings to provide further understanding of the disclosure, and attached drawing is included in the description and constitutes this Part of specification.
Fig. 1 is across the medium flight device power device jet-propulsion operation mode according at least one embodiment of the disclosure Structural schematic diagram.
Fig. 2 is across the medium flight device power device hydraulic jet propulsion operation mode according at least one embodiment of the disclosure Structural schematic diagram.
Fig. 3 is opened according to the model selection valve of across the medium flight device power device of the disclosure at least one embodiment Schematic diagram.
Fig. 4 is the model selection valve closure according to across the medium flight device power device of the disclosure at least one embodiment Schematic diagram.
Fig. 5 is to be pushed away according to the clutch of across the medium flight device power device of the disclosure at least one embodiment in jet Connection schematic diagram under into operation mode (by taking low-pressure turbine right side clutch as an example).
Fig. 6 is across the medium flight device power device clutch according to the disclosure at least one embodiment in hydraulic jet propulsion Connection schematic diagram under operation mode (by taking low-pressure turbine right side clutch as an example).
Specific embodiment
The disclosure is described in further detail with embodiment with reference to the accompanying drawing.It is understood that this place The specific embodiment of description is only used for explaining related content, rather than the restriction to the disclosure.It also should be noted that being Convenient for description, part relevant to the disclosure is illustrated only in attached drawing.
It should be noted that in the absence of conflict, the feature in embodiment and embodiment in the disclosure can To be combined with each other.The disclosure is described in detail below with reference to the accompanying drawings and in conjunction with embodiment.
In at least one embodiment of the disclosure, it is empty based on combustion chamber between grade and turbine water that present disclose provides one kind Shared across medium flight device power device, as depicted in figs. 1 and 2 comprising fanjet jet propulsion system is used for Power is provided to across medium flight device when airflight;Pump spray hydro-jet propulsion system, flies when for submariner under water to across medium The device that navigates provides power;And combustion chamber 9 and low-pressure turbine 11 between grade, it is pushed away for fanjet jet propulsion system and pump spray water spray It is shared into system.
According at least one embodiment of the disclosure, across medium flight device power device further includes clutch 12 and mode Selector valve 8, for realizing the conversion of fanjet jet propulsion system and pump spray hydro-jet propulsion system.
According at least one embodiment of the disclosure, as depicted in figs. 1 and 2, across medium flight device power device is also wrapped Turbomachinery adjustable mechanism 10 is included, for adjusting stator blade established angle, to meet fanjet jet propulsion system and pump respectively Spray the job requirement of hydro-jet propulsion system.
There are two types of operation modes for across the medium flight device power device tool that the disclosure provides: when flight device flies in the sky When, power device is with fanjet jet-propulsion Modality work;When flight device is in submariner, power device is pushed away with pumping spray water spray Into Modality work.When fanjet jet propulsion system works, low-pressure turbine 11 is sprayed by clutch 12 and fanjet The connection of gas propulsion system, model selection valve 8 is (Fig. 3) in the open state, so that fluid communication before low-pressure turbine 11;And pump spray When hydro-jet propulsion system works, low-pressure turbine 11 is connect by clutch 12 with pump spray hydro-jet propulsion system, at model selection valve 8 In closed state (Fig. 4), so that flow path seals before low-pressure turbine 11.
According at least one embodiment of the disclosure, as shown in Figure 1, fanjet jet propulsion system includes fan 2, For sucking and compressed air;High-pressure compressor 5 is used for compressed air, generates high pressure air;Main chamber 6, in main combustion It burns 6 high pressure air of room to mix with fuel, and ignition, generates combustion gas;And high-pressure turbine 7, it is pushed by combustion gas, simultaneously High-pressure turbine 7 is for driving high-pressure compressor 5.Fanjet jet propulsion system further include by-pass air duct 1, by-pass air duct supporting plate 3, Main duct 4.
As shown in Figure 1, low-pressure turbine 11 passes through clutch 12 and fan 2 when fanjet jet propulsion system works Connection.Combustion gas pushes low-pressure turbine 11 to rotate, and low-pressure turbine 11 is used for driving fan 2.The fuel of combustion chamber 9 is supplied as navigating between grade Empty kerosene, combustion chamber 9 is used to provide extra-push model to across medium flight device between grade.
Specifically, when flight device airflight, power device is with fanjet jet-propulsion Modality work.Low pressure whirlpool Wheel 11 is connect (Fig. 5) by clutch 12 with fan 2, and model selection valve 8 is (Fig. 3) in the open state, 9 fuel of combustion chamber between grade It is supplied as aviation kerosine, low-pressure turbine 11 adjusts stator blade established angle by Turbomachinery adjustable mechanism 10 to adapt to work under the mode It is required.Air dielectric compression through fan 2 after air inlet 17 is inhaled into power device is divided into two strands and respectively enters by-pass air duct 1 With main duct 4.Air-flow into by-pass air duct 1 is flowed directly to power device tail portion, is discharged via exhaust system, forms thrust.Into The air-flow for entering main duct 4 enters main chamber 6 after the further compression of high-pressure compressor 5, carries out with the aviation kerosine of penetrating Mixed combining combustion forms the combustion gas of high temperature and pressure.Then, combustion gas carries out expansion work to push high-pressure turbine 7 and low-pressure turbine 11, high-pressure turbine 7 and low-pressure turbine 11 respectively drive high-pressure compressor 5 and fan 2, finally still have the tail gas of certain energy and come It mutually converges from the air-flow of middle duct and is discharged together in power device tail portion, so that generating thrust realizes jet-propulsion.It is additional when needing When increasing thrust, combustion chamber 9 works between grade, and aviation kerosine is injected into combustion chamber 9 and the high-temperature high-pressure fuel gas flowed through between grade It is mixed and burned to promote fuel gas temperature, achievees the purpose that increase thrust.
According at least one embodiment of the disclosure, as shown in Fig. 2, pump spray hydro-jet propulsion system includes power output shaft 13, transmission mechanism and pump leaf 15;Wherein, power output shaft 13 is connect with one end of transmission mechanism;And pump leaf 15 and driver The other end of structure connects, the aqueous medium that pump leaf 15 is used to accelerate to suck from water inlet 18.Before pump spray hydro-jet propulsion system further includes Set stator 16.Transmission mechanism can be set to gear, further, can be set to helical gear 14.
As shown in Fig. 2, low-pressure turbine 11 passes through clutch 12 and power output shaft 13 when pump spray hydro-jet propulsion system work Connection.Propellant needed for the fuel supply of combustion chamber 9 is switched to underwater operation between grade, propellant combustion chamber 9 between grade are burnt, Combustion gas is generated, combustion gas pushes low-pressure turbine 11.Low-pressure turbine 11 drives power output shaft 13, and power output shaft 13 passes through driver Structure transfer tube leaf 15.
Specifically, when flight device enters water into when underwater submariner, power device turns from fanjet jet-propulsion mode Shift to pump spray hydraulic jet propulsion mode.After power device receives mode conversion signal, low-pressure turbine 11 passes through clutch 12 and wind Fan 2 disengages (Fig. 6), connect with power output shaft 13, the flow path before installation place rotatory sealing low-pressure turbine 11 of model selection valve 8 (Fig. 4), propellant needed for the supply of 9 fuel of combustion chamber switches to underwater operation as aviation kerosine between grade, low-pressure turbine 11 pass through Turbomachinery adjustable mechanism 10 is adjusted to adapt to the conversion of operation mode.At this point, as shown in Fig. 2, power device completes mode turn It changes and is started to work with pump spray hydraulic jet propulsion mode.Combustion chamber 9 is burnt between propellant is injected into grade, produced high pressure-temperature combustion gas 11 heel row of low-pressure turbine is pushed to go out power device, low-pressure turbine 11 drives power output shaft 13, and power output shaft 13 passes through two pairs Helical gear 14 drives pump leaf 15, after the aqueous medium that water inlet 18 is inhaled into is accelerated after the rectification of preposition stator 16 by pump leaf 15 Discharge, to realize hydraulic jet propulsion.
When the water outlet of flight device is again introduced into airflight, power device works from pump spray hydraulic jet propulsion mode to whirlpool Fan engine jet-propulsion mode conversion.After power device receives mode conversion signal, low-pressure turbine 11 passes through clutch 12 With 2 axis connection of fan, with power output shaft 13 disengage, model selection valve 8 around installation place rotarily open low-pressure turbine 11 before flow path (Fig. 3), the supply of 9 fuel of combustion chamber switches to aviation kerosine by propellant between grade, and low-pressure turbine 11 can by adjusting Turbomachinery Regulating mechanism 10 is to adapt to the conversion of operation mode.At this time as shown in Figure 1, power device completes mode conversion and with fanjet Jet-propulsion mode is started to work.
There are two types of operation modes for across the medium flight device power device tool that the disclosure provides: when flight device flies in the sky When, power device is with fanjet jet-propulsion Modality work;When flight device is in submariner, power device is pushed away with pumping spray water spray Into Modality work.Enter water, water outlet status according to flight device, power device carry out jet-propulsion mode and hydraulic jet propulsion mode it Between mode conversion.After receiving mode conversion instruction, flow path before the sealing of model selection valve 8 or unlatching low-pressure turbine 11, low pressure whirlpool Wheel 11 is connect by clutch 12 with power output shaft 13 or fan 2, and combustion chamber 9 switches different fuel supplies between grade, thus It realizes the mode conversion between fanjet hydraulic jet propulsion mode and pump spray hydraulic jet propulsion mode, is continuously across medium flight device Power is provided.In the sky when flight, high-speed flight is may be implemented with fanjet jet-propulsion Modality work in power device. Under water when submariner, pump of the power device in a manner of using heat power sprays hydraulic jet propulsion Modality work, and longer voyage may be implemented Submariner.
The power device introduces on the basis of traditional fanjet jet propulsion system and pump spray hydro-jet propulsion system The components such as combustion chamber 9, clutch 12 realize the unification of aerial and underwater heat power mode between model selection valve 8, grade, send out turbofan The components such as combustion chamber 9 and low-pressure turbine 11 between motivation jet propulsion system and pump spray hydro-jet propulsion system shared stage, effectively improve The utilization rate of component, alleviates the volume and weight of power device, keeps overall structure more compact.Meanwhile according to flight device Water outlet, enter regimen condition and carry out mode conversion between jet-propulsion mode and hydraulic jet propulsion mode, thus for flight device across Medium navigational duty provides lasting power.
It will be understood by those of skill in the art that above embodiment is used for the purpose of clearly demonstrating the disclosure, and simultaneously Non- be defined to the scope of the present disclosure.For those skilled in the art, may be used also on the basis of disclosed above To make other variations or modification, and these variations or modification are still in the scope of the present disclosure.

Claims (10)

1. a kind of across medium flight device power device shared based on combustion chamber between grade and turbine water sky, which is characterized in that described Across medium flight device power device includes
When fanjet jet propulsion system, the fanjet jet propulsion system are used for flight in the sky to it is described across Medium flight device provides power;
Pump spray hydro-jet propulsion system mentions when the pump spray hydro-jet propulsion system is for submariner under water to across the medium flight device For power;And
Combustion chamber and low-pressure turbine between grade, combustion chamber and the low-pressure turbine are the fanjet jet-propulsion between the grade System and pump spray hydro-jet propulsion system share.
2. across medium flight device power device according to claim 1, which is characterized in that across the medium flight device power Device further includes clutch and model selection valve, and the clutch and the model selection valve are for realizing the fanjet The conversion of jet propulsion system and the pump spray hydro-jet propulsion system.
3. across medium flight device power device according to claim 2, which is characterized in that
When the fanjet jet propulsion system works, the low-pressure turbine is started by the clutch and the turbofan The connection of machine jet propulsion system, the model selection valve is in the open state, so that fluid communication before the low-pressure turbine;And
When the pump spray hydro-jet propulsion system work, the low-pressure turbine sprays hydraulic jet propulsion system by the clutch and the pump System connection, the model selection valve are in close state, so that flow path seals before the low-pressure turbine.
4. across medium flight device power device according to claim 3, which is characterized in that the fanjet jet pushes away Include into system
Fan, the fan is for sucking and compressed air;
High-pressure compressor, the high-pressure compressor generate high pressure air for compressing the air;
Main chamber, the high pressure air described in the main chamber is mixed with fuel, and ignition, generates combustion gas;With And
High-pressure turbine, the high-pressure turbine are pushed by the combustion gas, while the high-pressure turbine is for driving the high pressure to calm the anger Machine.
5. across medium flight device power device according to claim 4, which is characterized in that the fanjet jet pushes away Into when system work, the low-pressure turbine is connect by the clutch with the fan, and the combustion gas pushes the low pressure whirlpool Wheel rotation, the low-pressure turbine is for driving the fan.
6. across medium flight device power device according to claim 4, which is characterized in that the fanjet jet pushes away Into when system work, the fuel of combustion chamber is aviation kerosine between the grade, and combustion chamber is used to fly to described across medium between the grade The device that navigates provides extra-push model.
7. across medium flight device power device according to claim 3, which is characterized in that the pump sprays hydro-jet propulsion system Including
Power output shaft, transmission mechanism and pump leaf;
Wherein, the power output shaft is connect with one end of the transmission mechanism;And
The pump leaf is connect with the other end of the transmission mechanism, the aqueous medium that the pump leaf is used to accelerate to suck from water inlet.
8. across medium flight device power device according to claim 7, which is characterized in that the pump sprays hydro-jet propulsion system When work, the low-pressure turbine passes through the clutch and the power output axis connection.
9. across medium flight device power device according to claim 8, which is characterized in that the pump sprays hydro-jet propulsion system When work, the fuel of combustion chamber is propellant needed for underwater operation, propellant combustion chamber between the grade between the grade Burning generates combustion gas, and the combustion gas pushes the low-pressure turbine, and the low-pressure turbine drives the power output shaft, described dynamic Power output shaft drives the pump leaf by the transmission mechanism.
10. across medium flight device power device according to claim 1, which is characterized in that across the medium flight device is dynamic Power device further includes Turbomachinery adjustable mechanism, and the Turbomachinery adjustable mechanism is for adjusting stator blade established angle, with full respectively The job requirement of the foot fanjet jet propulsion system and the pump spray hydro-jet propulsion system.
CN201910379186.9A 2019-05-08 2019-05-08 Cross-medium aircraft power device based on interstage combustion chamber and turbine water-air sharing Active CN110107426B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201910379186.9A CN110107426B (en) 2019-05-08 2019-05-08 Cross-medium aircraft power device based on interstage combustion chamber and turbine water-air sharing

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201910379186.9A CN110107426B (en) 2019-05-08 2019-05-08 Cross-medium aircraft power device based on interstage combustion chamber and turbine water-air sharing

Publications (2)

Publication Number Publication Date
CN110107426A true CN110107426A (en) 2019-08-09
CN110107426B CN110107426B (en) 2020-08-14

Family

ID=67488727

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201910379186.9A Active CN110107426B (en) 2019-05-08 2019-05-08 Cross-medium aircraft power device based on interstage combustion chamber and turbine water-air sharing

Country Status (1)

Country Link
CN (1) CN110107426B (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112483275A (en) * 2020-11-05 2021-03-12 邓云娣 Propeller and aircraft
CN112644235A (en) * 2021-01-08 2021-04-13 西北工业大学 Medium aircraft driving system is striden to repeatedly discrepancy water
CN112758334A (en) * 2021-01-28 2021-05-07 中南大学 Water-air cross-medium engine and cross-medium aircraft with same
CN113879052A (en) * 2021-10-22 2022-01-04 哈尔滨工程大学 Cross-medium water stamping power system and aircraft
CN114426101A (en) * 2022-01-29 2022-05-03 中国航发湖南动力机械研究所 Cross-medium power device
CN114576013A (en) * 2022-03-15 2022-06-03 清华大学 Method for cooling a turbine of an aircraft engine
CN115451427A (en) * 2022-09-01 2022-12-09 中国航发湖南动力机械研究所 Interstage combustion chamber and turbofan engine with same
WO2023124099A1 (en) * 2021-12-30 2023-07-06 北京国家新能源汽车技术创新中心有限公司 Dual-duct hybrid power device, flying vehicle, and control method

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012117365A1 (en) * 2011-03-02 2012-09-07 Frantisek Kreidl Fluid machine
CN204236156U (en) * 2014-11-21 2015-04-01 魏祥云 The all-round driving in a kind of land, water and air three
CN205150246U (en) * 2015-10-16 2016-04-13 天津汉海环保设备有限公司 Empty dual -purpose unmanned aerial vehicle of water
CN107792360A (en) * 2017-11-29 2018-03-13 周锦宇 Water air double-used aircraft
CN108891595A (en) * 2018-07-11 2018-11-27 中国航空发动机研究院 Across the medium flight device power device sealed using medium sensing device and duct
CN109519280A (en) * 2018-12-19 2019-03-26 哈尔滨工程大学 A kind of hybrid multistage power underwater bottom-sealing device of whirlpool paddle direct-injection and control method

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012117365A1 (en) * 2011-03-02 2012-09-07 Frantisek Kreidl Fluid machine
CN204236156U (en) * 2014-11-21 2015-04-01 魏祥云 The all-round driving in a kind of land, water and air three
CN205150246U (en) * 2015-10-16 2016-04-13 天津汉海环保设备有限公司 Empty dual -purpose unmanned aerial vehicle of water
CN107792360A (en) * 2017-11-29 2018-03-13 周锦宇 Water air double-used aircraft
CN108891595A (en) * 2018-07-11 2018-11-27 中国航空发动机研究院 Across the medium flight device power device sealed using medium sensing device and duct
CN109519280A (en) * 2018-12-19 2019-03-26 哈尔滨工程大学 A kind of hybrid multistage power underwater bottom-sealing device of whirlpool paddle direct-injection and control method

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
CN112644235A (en) * 2021-01-08 2021-04-13 西北工业大学 Medium aircraft driving system is striden to repeatedly discrepancy water
CN112758334A (en) * 2021-01-28 2021-05-07 中南大学 Water-air cross-medium engine and cross-medium aircraft with same
CN113879052A (en) * 2021-10-22 2022-01-04 哈尔滨工程大学 Cross-medium water stamping power system and aircraft
WO2023124099A1 (en) * 2021-12-30 2023-07-06 北京国家新能源汽车技术创新中心有限公司 Dual-duct hybrid power device, flying vehicle, and control method
CN114426101A (en) * 2022-01-29 2022-05-03 中国航发湖南动力机械研究所 Cross-medium power device
CN114426101B (en) * 2022-01-29 2023-11-17 中国航发湖南动力机械研究所 Cross-medium power device
CN114576013A (en) * 2022-03-15 2022-06-03 清华大学 Method for cooling a turbine of an aircraft engine
CN114576013B (en) * 2022-03-15 2024-03-26 清华大学 Turbine cooling method for aircraft engine
CN115451427A (en) * 2022-09-01 2022-12-09 中国航发湖南动力机械研究所 Interstage combustion chamber and turbofan engine with same
CN115451427B (en) * 2022-09-01 2023-10-27 中国航发湖南动力机械研究所 Interstage combustion chamber and turbofan engine with same

Also Published As

Publication number Publication date
CN110107426B (en) 2020-08-14

Similar Documents

Publication Publication Date Title
CN110107426A (en) Across the medium flight device power device shared based on combustion chamber between grade and turbine water sky
RU2448874C2 (en) Aircraft power plant
US8690099B2 (en) Aircraft and propulsion system
US10094235B2 (en) System, propulsion system and vehicle
US8684304B2 (en) Aircraft, propulsion system, and system for taxiing an aircraft
US7485981B2 (en) Aircraft combination engines complemental connection and operation
JP5325367B2 (en) Method and apparatus for operating a gas turbine engine
US8727270B2 (en) Aircraft, propulsion system, and system for taxiing an aircraft
US7690189B2 (en) Aircraft combination engines inlet airflow control system
CN203906118U (en) Gas cooling system for turbine-based combined-cycle engine
CN114787560B (en) Multi-mode combustion control for rotary detonation combustion systems
US20090113873A1 (en) Continously air breathing assisted jet engine linear aerospkie rocket
US11015476B2 (en) Electrical energy generating system
CN203906120U (en) Combined engine for unmanned combat aircraft
CN110107401A (en) Across medium flight device power device based on empty water flow passage compact layout
CN203906119U (en) Turbine-based combined cycle engine of wide flight envelope aircraft
CN105209741A (en) Thrust propulsion system
CN203547987U (en) Engine
RU2405959C1 (en) Method of gas generation for creation of thrust in air jet engine with multi-stage axial compressor and air jet engine
CN116945829A (en) Single-fuel-based cross-medium aircraft power system
CN116853474A (en) Mixed power water-air medium crossing engine based on fuel gas and electric power
CN203847274U (en) Core machine for turbine-based combined cycle engine
GB2612973A (en) Aircraft fuel cell propulsion unit with hybrid jet boost
CN117507703A (en) Cross-medium combined engine
Duva Use of navy external combustion engine technology: for ultra high altitude aircraft propulsion systems

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant